SUBROUTINE DEFTOL ( ARINPT, SW, CLTOA, CLAPP, ITAKOF, ILAND, TRR ) C INPUT DATA FOR THE TAKEOFF AND LANDING MODULE C FORMAL PARAMETERS ARE USED FOR DEFAULT VALUES C ARINPT REFERENCE ASPECT RATIO C SW REFERENCE WING AREA C CLTOA MAXIMUM TAKEOFF LIFT COEFFICIENT C CLAPP MAXIMUM APPROACH LIFT COEFFICIENT C ITAKOF DETAILED TAKEOFF SWITCH C ILAND DETAILED LANDING SWITCH C TRR REFERENCE THRUST FOR SCALING INPUT DATA IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /UNITS / IU5, IU6, IU7, IU8, IU9, IU16, IU17, IU18 COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO, CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON / LAND / ALMXLD,APRANG,CLLDM ,TISPOL,TIBRAK,CDMW ,DMO , 1 ACCLIM,DELTRN,OBSLD ,DELHAP,DELDFL,CDMLD ,APRHGT, 2 SWING, AR, THDRY, CLLD(10), CDLD(10), ALPLD(10), 3 MAGRUP COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /TREVRS/ RVFACT, TIRVRS, TIRVA, REVCTF, CLREV, CDREV, 1 VELRV(10), THRRV(10), INTHRV COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /NOISEP/ NOPRO, NPFILE, NOISE COMMON / FORT / IFITE COMMON /GEFSW / INCGEF COMMON /TAXFUL/ TAXOFL, ITXOUT DATA CDGEAR, CDEOUT /2*0./, FCDMTO /.3/, FCDMLD /-1./, 1 FTOCD, FLDCD /2*1./, REVCUT /-1000./ NAMELIST/TOLIN/ WHGT, SWREF, ARRET, APA, ALPRUN, TINC, CDGEAR, 1 ITIME, TIGEAR, CLSPOL, CDSPOL, BRAKMU, ROLLMU, 2 CLTOM, ALMXTO, CDMTO, FCDMTO, ALPTO, CLTO, CDTO, 3 INTHTO, VELTO, THRTO, VROTAT, ALPROT, THFACT, 4 CDDP, CLDPOC, TISPA, TIBRA, TICUT, OBSTO, IBAL, 5 DELTRO, DELVTO, CLLDM, ALMXLD, CDMLD, FCDMLD, 6 ALPLD, CLLD, CDLD, VELLD, THRLD, INTHLD, OBSLD, 7 TISPOL, TIBRAK, APRANG, ACCLIM, DELHAP, DELDFL, 8 DELTRN, APRHGT, VANGL, DELTCL, DTCT, INTHRV, 9 VELRV, THRRV, RVFACT, TIRVRS, TIRVA, ARGEF, * PILOTT, ISPOL, IREV, NOPRO, NOISE, CDEOUT, THDRY, 1 INCGEF, FTOCD, FLDCD, MAGRUP, ITXOUT, REVCUT, 2 CLREV, CDREV ARRET = ARINPT SWREF = SW THREF = TRR CLTOM = CLTOA CLLDM = CLAPP OBSTO = 35. + 15.*IFITE MAGRUP = IFITE C READ NAMELIST TOLIN READ ( IU5, NML=TOLIN, ERR=9000, END=9000 ) SWING = SWREF AR = ARRET CDMT = FCDMTO * CDMTO DMT = (1.0 - FCDMTO) * CDMTO * SWREF DO 10 I = 1,10 THRTO(I) = THRTO(I) * THFACT CDTO (I) = CDTO (I) * FTOCD CDLD (I) = CDLD (I) * FLDCD 10 CONTINUE IF ( THRTO(1) .LE. 0.0 .AND. INTHTO .LT. 2 ) INTHTO = 2 IF ( FCDMLD .LT. 0.0 ) FCDMLD = FCDMTO CDMW = FCDMLD * CDMLD DMO = (1.0 - FCDMLD) * CDMLD * SWREF CDGRO = CDGEAR * SWREF CDEOT = CDEOUT * SWREF IF ( APRHGT .LE. 100.0 ) APRHGT = 100.001 IF ( APRANG .GT. 0.0 ) APRANG = -APRANG IF ( NOISE .EQ. 1 ) NOPRO = 1 C PRINT INPUT DATA WRITE(IU6, 20) APA, DTCT, SWREF, ARRET, WHGT, ALPRUN, TINC, 1 ROLLMU, BRAKMU, VANGL, CDGEAR, CDEOUT, CLSPOL, 2 CDSPOL, INCGEF, ARGEF, ITIME IF ( ITAKOF .EQ. 0 ) GO TO 60 WRITE(IU6, 40) CLTOM, CDMTO, FCDMTO, ALMXTO, OBSTO, ALPROT, 1 VROTAT, THFACT, FTOCD, TIGEAR, PILOTT, DELVTO, 2 DELTRO, DELTCL, IBAL, ISPOL, IREV, INTHTO, ITXOUT WRITE(IU6, 50) (ALPTO(I), I = 1,10), (CLTO(I), I = 1,10), 1 (CDTO(I), I = 1,10), (VELTO(I), I = 1,10), 2 (THRTO(I), I = 1,10), (CLDPOC(I),I = 1,10), 3 (CDDP(I), I = 1,10) IF ( ILAND .EQ. 0 ) GO TO 90 60 WRITE(IU6, 70) CLLDM, CDMLD, FCDMLD, ALMXLD, OBSLD, APRHGT, 1 APRANG, FLDCD, TISPOL, TICUT, TIBRAK, ACCLIM, 2 MAGRUP, DELHAP, DELDFL, DELTRN, INTHLD IF ( IFITE .EQ. 1 .AND. THDRY .GT. 0. ) WRITE(IU6, 75) THDRY WRITE(IU6, 80) (ALPLD(I), I = 1,10), (CLLD(I), I = 1,10), 1 (CDLD(I), I = 1,10), (VELLD(I), I = 1,10), 2 (THRLD(I), I = 1,10) 90 IF ( RVFACT .EQ. 0. ) GO TO 110 WRITE(IU6,100) RVFACT, TIRVRS, REVCUT, CLREV, CDREV, INTHRV, 1 (VELRV(I), I = 1,10), (THRRV(I), I = 1,10) REVCTF = REVCUT*1852./.3048/3600. 110 IF ( NOPRO .EQ. 1 ) WRITE(IU6, 30) IF ( NOISE .EQ. 1 ) WRITE(IU6, 31) RETURN 20 FORMAT (///'# NAMELIST $TOLIN',/ 1 ' DETAILED TAKEOFF AND LANDING INPUT DATA',// 2 ' DESCRIPTION',16X,'NAME',9X,'VALUE DIMENSIONS',// 3 ' AIRPORT ALTITUDE APA ',F11.0,' FT',/ 4 ' DELTA TEMPERATURE DTCT ',F11.1,' DEG C',/ 5 ' REFERENCE WING AREA SWREF ',F11.1,' SQ FT',/ 6 ' REFERENCE ASPECT RATIO ARRET ',F11.4,/ 7 ' WING HEIGHT ABOVE GROUND WHGT ',F11.2,' FT',/ 8 ' ANGLE OF ATTACK ON GROUND ALPRUN ',F11.2,' DEG',/ 9 ' THRUST INCIDENCE ON GRND TINC ',F11.2,' DEG',/ * ' COEF. OF ROLLING FRICTION ROLLMU ',F11.4,/ 1 ' COEF. OF FRICTION W/BRAKES BRAKMU ',F11.4,/ 2 ' ROTATION OR FLARE RATE VANGL ',F11.4,' DEG/SEC',/ 3 ' LANDING GEAR DRAG COEF. CDGEAR ',F11.6,/ 4 ' ENGINE OUT DELTA CD CDEOUT ',F11.6,/ 5 ' SPOILER LIFT COEFFICIENT CLSPOL ',F11.6,/ 6 ' SPOILER DRAG COEFFICIENT CDSPOL ',F11.6,/ 7 ' GROUND EFFECTS SWITCH INCGEF ',I11,/ 8 ' AR FACTOR FOR GRND EFF. ARGEF ',F11.5,/ 9 ' PROFILE PRINT SWITCH ITIME ',I11) 30 FORMAT (/' A DETAILED TAKEOFF PROFILE FOR NOISE CALCULATIONS WILL' 1 ,' BE GENERATED') 31 FORMAT (/' NOISE CALCULATIONS WILL BE PERFORMED') 40 FORMAT (/' INPUT DATA FOR TAKEOFF',/ 1 ' MAXIMUM LIFT COEFFICIENT CLTOM ',F11.6,/ 2 ' MINIMUM DRAG COEFFICIENT CDMTO ',F11.6,/ 3 ' WING FRACTION OF CDMTO FCDMTO ',F11.5,/ 4 ' MAXIMUM ANGLE OF ATTACK ALMXTO ',F11.2,' DEG',/ 5 ' OBSTACLE HEIGHT OBSTO ',F11.2,' FT',/ 6 ' MAX ALPHA DURING ROTATION ALPROT ',F11.2,' DEG',/ 7 ' ROTATION VELOCITY',10X,'VROTAT ',F11.3,' KTS OR % VSTALL',/ 8 ' THRUST MULTIPLIER THFACT ',F11.5,/ 9 ' TAKEOFF DRAG FACTOR FTOCD ',F11.4,/ * ' TIME REQ. TO RAISE GEAR TIGEAR ',F11.2,' SEC',/ 1 ' PILOT REACTION TIME PILOTT ',F11.2,' SEC',/ 2 ' GROUND RUN VELOCITY STEP DELVTO ',F11.2,' FT/SEC',/ 3 ' ROTATION TIME STEP DELTRO ',F11.3,' SEC',/ 4 ' CLIMBOUT TIME STEP DELTCL ',F11.3,' SEC',/ 5 ' BALANCED FIELD LENGTH ? IBAL ',I11,/ 6 ' SPOILERS DURING ABORT ? ISPOL ',I11,/ 7 ' ABORT THRUST REV. OPTION IREV ',I11,/ 8 ' THRUST INPUT OPTION INTHTO ',I11,/ 9 ' TAXI OUT FUEL SWITCH ITXOUT ',I11) 50 FORMAT (/' TAKEOFF DRAG POLAR - GEAR DRAG NOT INCLUDED',// 1 ' ANGLE OF ATTACK ALPTO ',10F10.2,/ 2 ' LIFT COEFFICIENT CLTO ',10F10.6,/ 3 ' DRAG COEFFICIENT CDTO ',10F10.6,// 4 ' INPUT NET THRUST VALUES PER ENGINE DURING TAKEOFF',/ 5 ' VELOCITY, FT/SEC VELTO ',10F10.1,/ 6 ' THRUST, LB THRTO ',10F10.1,// 7 ' VELOCITY DEPENDENT LIFT AND DRAG DURING TAKEOFF',/ 8 ' LIFT COEFFICIENT CLDPOC',10F10.6,/ 9 ' DRAG COEFFICIENT CDDP ',10F10.6) 70 FORMAT (/' INPUT DATA FOR LANDING',/ 1 ' MAXIMUM LIFT COEFFICIENT CLLDM ',F11.6,/ 2 ' MINIMUM DRAG COEFFICIENT CDMLD ',F11.6,/ 3 ' WING FRACTION OF CDMLD FCDMLD ',F11.5,/ 4 ' MAXIMUM ANGLE OF ATTACK ALMXLD ',F11.2,' DEG',/ 5 ' OBSTACLE HEIGHT OBSLD ',F11.2,' FT',/ 6 ' START APPROACH HEIGHT APRHGT ',F11.2,' FT',/ 7 ' APPROACH FLIGHT PATH ANGLE APRANG ',F11.2,' DEG',/ 8 ' LANDING DRAG FACTOR FLDCD ',F11.4,/ 9 ' TIME TO SPOILER ACTUATION TISPOL ',F11.2,' SEC',/ * ' TIME TO ENGINE CUTBACK TICUT ',F11.2,' SEC',/ 1 ' TIME TO BRAKE APPLICATION TIBRAK ',F11.2,' SEC',/ 2 ' DECELERATION LIMIT ACCLIM ',F11.2,' FT/SEC2',/ 3 ' MISSED APPROACH GEAR UP MAGRUP ',I11,/ 4 ' APPROACH ALTITUDE STEP DELHAP ',F11.2,' FT',/ 5 ' FLARE DISTANCE STEP DELDFL ',F11.2,' FT',/ 6 ' RUNOUT TIME STEP DELTRN ',F11.2,' SEC',/ 7 ' THRUST INPUT OPTION INTHLD ',I11) 75 FORMAT ( ' MAXIMUM DRY THRUST THDRY ',F10.1,' LB') 80 FORMAT (/' LANDING DRAG POLAR - GEAR DRAG NOT INCLUDED',// 1 ' ANGLE OF ATTACK ALPLD ',10F10.2,/ 2 ' LIFT COEFFICIENT CLLD ',10F10.6,/ 3 ' DRAG COEFFICIENT CDLD ',10F10.6,// 4 ' INPUT NET THRUST VALUES PER ENGINE DURING LANDING',/ 5 ' VELOCITY, FT/SEC VELLD ',10F10.1,/ 6 ' THRUST, LB THRLD ',10F10.1) 100 FORMAT(/' INPUT DATA FOR THRUST REVERSAL',// 1 ' THRUST REVERSAL FRACTION RVFACT ',F11.5,/ 2 ' TIME AFTER TOUCHDOWN TIRVRS ',F11.2,' SEC',/ 3 ' REVERSER CUTOFF VELOCITY REVCUT ',F11.1,' KTS',/ 4 ' DELTA LIFT COEFFICIENT CLREV ',F11.5,/ 5 ' DELTA DRAG COEFFICIENT CDREV ',F11.5,/ 6 ' THRUST INPUT OPTION INTHRV ',I11,// 7 ' INPUT NET THRUST VALUES PER ENGINE DURING REVERSAL',/ 8 ' VELOCITY, FT/SEC VELRV ',10F10.1,/ 9 ' THRUST, LB THRRV ',10F10.1) 9000 WRITE(IU6,9001) IU5 9001 FORMAT (//' ERROR READING NAMELIST $TOLIN FROM UNIT',I3,/, 2 ' PROGRAM ABORTED IN SUBROUTINE DEFTOL.',/) STOP END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC BLOCK DATA TLNMIN IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) C DEFAULT VALUES FOR TAKEOFF AND LANDING INPUT DATA (NAMELIST $TOLIN) COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO , CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON / LAND / ALMXLD,APRANG,CLLDM ,TISPOL,TIBRAK,CDMW ,DMO , 1 ACCLIM,DELTRN,OBSLD ,DELHAP,DELDFL,CDMLD ,APRHGT, 2 SWING, AR, THDRY, CLLD(10), CDLD(10), ALPLD(10), 3 MAGRUP COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /TREVRS/ RVFACT, TIRVRS, TIRVA, REVCUT, CLREV, CDREV, 1 VELRV(10), THRRV(10), INTHRV COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /ROTSPD/ VROT, VEE2 COMMON /PRAERO/ ALPRO(10,10), CLPRO(10,10), CDPRO(10,10), 1 DFLAP(10), TXF, ALPMIN, GAMLIM COMMON /NOISEP/ NOPRO, NPFILE, NOISE COMMON /TAXFUL/ TAXOFL, ITXOUT COMMON /GEFSW / INCGEF DATA VELTO/0.0,50.,100.,150.,200.,250.,300.,350.,400.,450./, 1 ALPRUN, TINC, CDMTO, THRTO/13*0./, ALPROT, ALMXTO/2*25./, 2 ITIME, INTHTO/2*0/, VROTAT/1.05/, THFACT/1./, WHGT/8./, 3 TIGEAR/2./, CDDP, CLDPOC/20*0./, APRHGT/100.001/, 4 IBAL, ISPOL, IREV/3*1/, DELTRO/.2/, DELVTO/4./, ALMXLD/25./, 5 VELLD/0.,50.,100.,150.,200.,250.,300.,350.,400.,450./, 6 OBSLD/50./, CLSPOL, CDSPOL, APA, CDMLD, THRLD, DTCT/15*0./, 7 TISPA, TIBRA, TICUT/3*3./, BRAKMU/.3/, ROLLMU/.025/, 8 VANGL, TISPOL/2*2./, TIBRAK/4./, ACCLIM/16./, PILOTT/1./, 9 DELHAP/10./, DELDFL/10./, DELTRN/.25/, DELTCL/.2/, ARGEF/1./, * INTHLD/0/, THDRY/0./, APRANG/-3./, INCGEF/1/, ITXOUT/0/ DATA VELRV/0.0,50.,100.,150.,200.,250.,300.,350.,400.,450./, 1 THRRV, RVFACT, CLREV, CDREV/13*0./, INTHRV/-1/, TIRVRS/5./, 2 TIRVA/1000./, REVCUT/-1000./, 3 ALPTO, ALPLD, CDTO, CDLD, CLTO, CLLD/60*0./, 4 VROT, VEE2, ALPMIN/3*0./, GAMLIM/0./, 5 ALPRO, CLPRO, CDPRO /300*0./, 6 DFLAP /1.,2.,3.,4.,5.,6.,7.,8.,9.,10./, 7 NOPRO, NPFILE, NOISE /3*0/, TAXOFL /0./, TXF /-1./ END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE TOFF (FAROFF,RMPWT,IPRNT,ARN,SW,GLOV,NENG,FORCE2) C EVALUATE ENGINE-OUT SECOND SEGMENT CLIMB GRADIENT CONSTRAINT C COMPUTE TAKEOFF PROFILE AND FIELD LENGTH C COMPUTE BALANCED FIELD LENGTH IF REQUESTED C FAROFF = TAKEOFF OR BALANCED FIELD LENGTH C GROSWT = AIRCRAFT CURRENT RAMP WEIGHT C IPRNT = PRINT SWITCH C ARN,SW,GLOV = CURRENT ASPECT RATIO, WING AREA, AND GLOVE AREA C NENG = NUMBER OF ENGINES C FORCE2 = THRUST SURPLUS AFTER MEETING SECOND SEGMENT CLIMB C GRADIENT (IF NEGATIVE, DELTA THRUST REQUIRED) C KEY CONTROL INTEGERS C IBAL = 1, PERFORM BALANCED FIELD LENGTH CALCULATIONS C ITER = BALANCED FIELD LENGTH ITERATION COUNTER IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /UNITS / IU5, IU6, IU7, IU8, IU9, IU16, IU17, IU18 COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO, CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON /SCRTCH/ TG(125,2), DG(125,2), VG(125,2), THG(125,2), 1 CGL(125,2), CGD(125,2), ACG(125,2), TS(125,2), 2 DS(125,2), VS(125,2), THS(125,2), CSL(125,2), 3 CSD(125,2), ACS(125,2), TR(250), DR(250), VR(250), 4 ALR(250), THR(250), CLR(250), CDR(250), ACR(250), 5 T(250), D(250), ALT(250), V(250), GAM(250), 6 ALP(250), TH(250), CLL(250), CDD(250), ACL(250), 7 KDUM(3200) COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /ROTDAT/ VTR(2), ALFROT, ALPMAX, CDGEAR, CDEOUT, SPAN, 1 VSTALL, V005, NE, IFAIL, ICRIT, ILAG COMMON /ROTSPD/ VROT, VEE2 COMMON / FORT / IFITE COMMON /TAXFUL/ TAXOFL, ITXOUT DIMENSION IRUN(2), ISTP(2) DATA RAD /0.0174533/ C SCALE AERODYNAMIC DRAG ASSUMING PARABOLIC POLAR C INITIALIZE CONSTANTS AND CONFIGURATION DATA SPAN = SQRT( ARN * (SW - GLOV) ) CDM = CDMT + DMT / SW GROSWT = RMPWT - ITXOUT*TAXOFL DO 10 I = 1,10 CDTO(I) = (CDTO(I) - CDMTO) * ARRET / ARN + CDM 10 CONTINUE CDGEAR = CDGRO / SW CDEOUT = CDEOT / SW CDMTO = CDM ARRET = ARN SWREF = SW ZERO = 0. DBAL = 0. VSTR = 0. VSSR = 0. VTR(1) = 0. VTR(2) = 0. VRM5 = 0. VEFR = 0. FFCT = 1.15 - 0.15*IFITE IFCT = FFCT*100.01 C PRINT CURRENT DRAG POLAR AND THRUST SCHEDULE IF ( IPRNT .LE. 0 ) GO TO 15 WRITE(IU6, 510) WRITE(IU6, 520) (ALPTO(I), I = 1,10) WRITE(IU6, 530) (CLTO (I), I = 1,10) WRITE(IU6, 540) (CDTO (I), I = 1,10) WRITE(IU6, 545) CDMTO, CDGEAR, CDEOUT, CLTOM, GROSWT WRITE(IU6, 550) WRITE(IU6, 560) (VELTO(I), I = 1,10) WRITE(IU6, 570) (THRTO(I), I = 1,10) 15 SPD = 1852./(.3048*3600.) NE = NENG IF ( NE .EQ. 1 ) IBAL = 0 RHOA = ANS1 * SW * 0.5 VSTALL = SQRT( GROSWT / (CLTOM * RHOA) ) / SPD VRTATE = VSTALL CALL ORIDE (VRTATE,VROTAT) VOSREQ = 1.2 * VSTALL VROT = VRTATE * SPD VEND = 1.5 * VSTALL * SPD IF ( VROT .GT. VEND ) VEND = VROT C CONSTRAIN FIGHTER TAKEOFF SPEED TO BE GREATER THAN OR EQUAL TO C THE SPEED FOR A .5 PERCENT CLIMB GRADIENT - ONE ENGINE OUT IF ( IFITE .EQ. 0 ) GO TO 17 GAM2 = .005 SG = SIN( GAM2 ) CG = COS( GAM2 ) C V005 MUST BE .GE. 1.1 VSTALL V005 = 1.1 * VSTALL * SPD IRR = 0 ILAG = 2 C DETERMINE IF CLIMB GRADIENT IS MET AT 1.1 VSTALL 21 NEOP = NE - 1 IF ( NE .EQ. 1 ) NEOP = 1 THRU = XINT1( V005,VELTO,10,THRTO ) * NEOP CALL CLGRAD ( V005, RHOA, THRU, GROSWT, CG, SG, ALPTO, CLTO, CDTO, 1 ZERO, CDEOUT, ALPRUN, TINC, RAD, ALP2, FORCE2 ) IF ( IRR .GT. 1 ) GO TO 31 IF ( FORCE2 .GT. 0.0 ) GO TO 17 FEPS = 0.0000001*THRU C INCREASE V005 UNTIL CRITERION IS MET C FIRST ITERATION IRR = 2 ILAG = 3 VO = V005 FORO = FORCE2 V005 = 1.05 * V005 GO TO 21 C SUBSEQUENT ITERATIONS 31 IRR = IRR + 1 IF ( ABS(FORCE2-FEPS) .LT. FEPS .OR. IRR .GT. 15 ) GO TO 17 DELV = (V005 - VO) * (FORCE2 - FEPS) / (FORO - FORCE2) IF ( ABS(DELV) .GT. 5.*SPD ) DELV = SIGN( 5.*SPD, DELV) C IF DIRECTION IS WRONG, HALVE INTERVAL IF ( DELV*FORCE2 .LT. 0. ) GO TO 36 V005 = (VO + V005) / 2. GO TO 21 36 VO = V005 FORO = FORCE2 V005 = V005 + DELV GO TO 21 C SET UP GROUND RUN TABLES c ohad 16/7/08 - 0.0d0 rather than 0. c 17 CALL GEFECT ( ALPRUN, 0. , 0., ALPTO, CLTO, CDTO, CDMTO, CL, CDG, c 1 ARRET*ARGEF, WHGT, SPAN ) 17 CALL GEFECT ( ALPRUN, 0.0d0 , 0.0d0, 1 ALPTO, CLTO, CDTO, CDMTO, CL, CDG, 1 ARRET*ARGEF, WHGT, SPAN ) CDG = CDG + CDGEAR CALL GRRUN ( VEND, NE, GROSWT, CDG, CL, IRUN, CDEOUT ) C FIND ROTATION SPEED TO MEET MINIMUM UNSTICK REQUIREMENTS AND C DETERMINE PROFILE FROM ROTATION TO OBSTACLE ALPMAX = XINT1( CLTOM/1.44, CLTO, 10, ALPTO ) IF ( ALPMAX .GT. ALMXTO) ALPMAX = ALMXTO ALFROT = ALPROT IF ( ALFROT .GT. ALPMAX ) ALFROT = ALPMAX IF ( IBAL .EQ. 0 ) GO TO 310 ICRIT = 0 IFAIL = 0 CALL ROTCL ( VROT, GROSWT, DLO, TLO, VLO, ALLO, ILO, DOBST, TOBST, 1 VOBST, ALOST, GAOST, IOBST ) IF ( IFAIL .EQ. 2 ) GO TO 400 C SET UP DECELERATION TO STOP TABLES CALL DECEL ( VEND, NE, GROSWT, CDG, CL, ISTP ) C SECOND SEGMENT CLIMB GRADIENT CALCULATIONS - ONE ENGINE OUT C CALCULATE REQUIRED CLIMB GRADIENT - GAM2 GAM2 = ATAN( 0.018 + 0.003 * NE ) IF ( IFITE .EQ. 1 ) GAM2 = 0.025 SG = SIN( GAM2 ) CG = COS( GAM2 ) C VOBST MUST BE .GE. 1.2 VSTALL V2 = VOBST * SPD IRR = 0 IF ( V2 .GE. VOSREQ*SPD .AND. IFAIL .EQ. 0 ) GO TO 20 V2 = VOSREQ * SPD IRR = 1 VSTR = 1. C DETERMINE NET THRUST IF CLIMB GRADIENT IS MET 20 NEOP = NE - 1 IF ( NE .EQ. 1 ) NEOP = 1 THRU = XINT1( V2,VELTO,10,THRTO ) * NEOP CALL CLGRAD ( V2, RHOA, THRU, GROSWT, CG, SG, ALPTO, CLTO, CDTO, 1 ZERO, CDEOUT, ALPRUN, TINC, RAD, ALP2, FORCE2 ) IF ( IRR .GT. 1 ) GO TO 30 IF ( FORCE2 .GT. 0.0 ) GO TO 40 FEPS = 0.0000001*THRU C SECOND SEGMENT CLIMB GRADIENT CRITERION FAILED C INCREASE V2 UNTIL CRITERION IS MET C FIRST ITERATION IRR = 2 VO = V2 FORO = FORCE2 V2 = 1.05 * V2 GO TO 20 C SUBSEQUENT ITERATIONS 30 IRR = IRR + 1 IF ( ABS(FORCE2-FEPS) .LE. FEPS .OR. IRR .GT. 20 ) GO TO 40 DELV = (V2 - VO) * (FORCE2 - FEPS) / (FORO - FORCE2) IF ( ABS(DELV) .GT. 5.*SPD ) DELV = SIGN( 5.*SPD, DELV) C IF DIRECTION IS WRONG, HALVE INTERVAL IF ( DELV*FORCE2 .LT. 0. ) GO TO 35 V2 = (VO + V2) / 2. GO TO 20 35 VO = V2 FORO = FORCE2 V2 = V2 + DELV GO TO 20 C IF V2 HAS CHANGED, DETERMINE ROTATION SPEED SUCH THAT C V2 IS REACHED AT THE OBSTACLE WITH ONE ENGINE OUT 40 IF ( IRR .EQ. 0 ) GO TO 60 M = 0 ICRIT = 2 DVR = (V2 - VOBST * SPD) * 1.5 50 VO = VROT VOO = VOBST * SPD VROT = VO + DVR IFAIL = 0 CALL ROTCL ( VROT, GROSWT, DLO, TLO, VLO, ALLO, ILO, DOBST, TOBST, 1 VOBST, ALOST, GAOST, IOBST ) M = M + 1 DVR = V2 - VOBST * SPD IF ( (VOBST*SPD - VOO) .GT. .01 ) 1 DVR = (VROT - VO) * (V2 - VOBST*SPD) / (VOBST*SPD - VOO) IF ( ABS(DVR) .GT. 5.*SPD ) DVR = SIGN( 5.*SPD, DVR) IF ( ABS(DVR) .GT. .0001 .AND. M .LT. 15 ) GO TO 50 IF ( VSTR .GT. 0. ) VSTR = VROT IF ( IRR .GT. 1 ) VSSR = VROT IF ( IFAIL .GT. 0 ) GO TO 400 C TABULAR DATA HAS BEEN DEFINED, SATISFY FAR PART 25.107(E)(3) C FIND TAKEOFF DISTANCE FOR ROTATION SPEED VRT5 = VROT - 5 KNOTS 60 SROT = VROT IF ( IFITE .EQ. 1 ) GO TO 110 ITER = 0 80 VRT5 = VROT - 5. * SPD IRT5 = 1 + VRT5 / DELVTO IF ( IRT5 .GE. IRUN(2) ) IRT5 = IRUN(2) - 1 DTR5 = 1. + VRT5 / DELVTO - IRT5 DRT5 = DG(IRT5,2) * (1.-DTR5) + DG(IRT5+1,2) * DTR5 C CALCULATE ROTATION AND CLIMB-TO-OBSTACLE DISTANCE STARTING C AT ROTATION SPEED VRT5 ICRIT = 2 IFAIL = 0 CALL ROTCL ( VRT5, GROSWT, DLO5, TLO5, VLO5, ALO5, ILO5, DOBS5, 1 TOBS5, VOBS5, ALOS5, GAOS5, IOBS5 ) DTO5 = DOBS5 C CALCULATE GROUND RUN, ROTATION AND CLIMB-TO-OBSTACLE DISTANCE C STARTING AT VRT5 AND ROTATING AT VROT IRT = 1 + VROT / DELVTO IF ( IRT .GE. IRUN(2) ) IRT = IRUN(2) - 1 DTRT = 1. + VROT / DELVTO - IRT DRT2 = DG(IRT,2) * (1.-DTRT) + DG(IRT+1,2) * DTRT DROT = DRT2 - DRT5 C RECALCULATE ROTATION AND CLIMB TO OBSTACLE CALL ROTCL ( VROT, GROSWT, DLO, TLO, VLO, ALLO, ILO, DOBST, TOBST, 1 VOBST, ALOST, GAOST, IOBST ) DTO2 = DROT + DOBST IF ( IFITE .EQ. 1 ) DTO2 = DROT + DLO C IF TAKEOFF DISTANCE WITH EARLY ROTATION IS GREATER THAN THAT C AT NORMAL ROTATION, INCREASE VROT UNTIL THEY ARE EQUAL DELDE = DTO5 - DTO2 IF ( ITER .GT. 0 ) GO TO 90 IF ( DELDE .LT. .1 ) GO TO 110 DELV2 = 5. * SPD GO TO 100 90 IF ( ABS(DELDE) .LT. .1 .OR. ITER .GT. 9 ) GO TO 110 DELV2 = DELV2 * DELDE / ( DELDO - DELDE ) IF ( ABS(DELV2) .GT. 5.*SPD ) DELV2 = SIGN( 5.*SPD, DELV2) 100 ITER = ITER + 1 DELDO = DELDE VROT = VROT + DELV2 VRM5 = VROT GO TO 80 C FIRST GUESS AT ENGINE FAILURE VELOCITY - VEF = VROT - 5 KNOTS C IF THIS IS TOO LOW, VROT WILL HAVE TO BE REDEFINED TO MEET C FAR PART 25.107(E)(3) WHICH REQUIRES TAKEOFF WITH ONE ENGINE C OUT AT A ROTATION SPEED 5 KNOTS LESS THAN VROT 110 IF ( IFAIL .GT. 0 ) GO TO 400 IF ( NE .EQ. 1 ) GO TO 310 VEF = VROT - 5.*SPD*(1-IFITE) IREC = 0 ITER = 0 C ENSURE THAT VROT WILL NOT BE LESS THAN V1 - THE DECISION SPEED IRT = 1 + VROT / DELVTO IF ( IRT .GE. IRUN(2) ) IRT = IRUN(2) - 1 DTRT = 1. + VROT / DELVTO - IRT DECT = PILOTT*(1-IFITE) + 3.*IFITE TAVF = TG(IRT,2) * (1.-DTRT) + TG(IRT+1,2) * DTRT - DECT IVF = IRT 120 IF ( TG(IVF,2) .LE. TAVF ) GO TO 130 IVF = IVF - 1 GO TO 120 130 DAVF = (TAVF - TG(IVF,2)) / (TG(IVF+1,2) - TG(IVF,2)) VTRY = VG(IVF,2) * (1.-DAVF) + VG(IVF+1,2) * DAVF IF (VTRY .LT. VEF ) VEF = VTRY C ACCELERATE-STOP DISTANCE, FAR PART 25.109 C FIND ENGINE FAILURE DISTANCES AND DECISION SPEED TIME 140 IEF = 1 + VEF / DELVTO IF ( IEF .GE. IRUN(2) ) IEF = IRUN(2) - 1 DTEF = 1. + VEF / DELVTO - IEF DEF2 = DG(IEF,2) * (1.-DTEF) + DG(IEF+1,2) * DTEF DEF1 = DG(IEF,1) * (1.-DTEF) + DG(IEF+1,1) * DTEF DDEF = DEF2 - DEF1 TV1 = TG(IEF,2) * (1.-DTEF) + TG(IEF+1,2) * DTEF + PILOTT IV1 = IEF C FIND DECISION SPEED - V1 150 IF ( TG(IV1+1,2) .GT. TV1 ) GO TO 160 IV1 = IV1 + 1 GO TO 150 160 IF ( IV1 .GE. IRUN(2) ) IV1 = IRUN(2) - 1 DTV1 = (TV1 - TG(IV1,2)) / (TG(IV1+1,2) - TG(IV1,2)) V1 = VG(IV1,2) * (1.-DTV1) + VG(IV1+1,2) * DTV1 C FIND TIME, VELOCITY AND DISTANCE AT START OF BRAKING FOR C ONE ENGINE OUT - TB2, VB2 AND DB2 TB2 = TV1 + 2. IB2 = IV1 170 IF ( TG(IB2+1,2) .GT. TB2 ) GO TO 180 IB2 = IB2 + 1 GO TO 170 180 IF ( IB2 .GE. IRUN(2) ) IB2 = IRUN(2) - 1 DTB2 = (TB2 - TG(IB2,2)) / (TG(IB2+1,2) - TG(IB2,2)) VB2 = VG(IB2,2) * (1.-DTB2) + VG(IB2+1,2) * DTB2 DB2 = DG(IB2,2) * (1.-DTB2) + DG(IB2+1,2) * DTB2 - DDEF C FIND STOPPING DISTANCE FROM A VELOCITY OF VB2 TST2 = TS(IB2,2) * (1.-DTB2) + TS(IB2+1,2) * DTB2 DST2 = DS(IB2,2) * (1.-DTB2) + DS(IB2+1,2) * DTB2 C FIND TOTAL ACCELERATE-STOP DISTANCE - ONE ENGINE OUT DAS2 = DB2 + DST2 IF ( IFITE .EQ. 1 ) THEN DAS = DAS2 DAS1 = 0. GO TO 205 ENDIF C FIND TIME AT V1 AND TIME, VELOCITY AND DISTANCE AT START OF C BRAKING FOR ALL ENGINES OPERATING - TB1, VB1 AND DB1 TB1 = TG(IV1,1) * (1.-DTV1) + TG(IV1+1,1) * DTV1 + 2. IB1 = IV1 190 IF ( TG(IB1+1,1) .GT. TB1 ) GO TO 200 IB1 = IB1 + 1 GO TO 190 200 IF ( IB1 .GE. IRUN(1) ) IB1 = IRUN(1) - 1 DTB1 = (TB1 - TG(IB1,1)) / (TG(IB1+1,1) - TG(IB1,1)) VB1 = VG(IB1,1) * (1.-DTB1) + VG(IB1+1,1) * DTB1 DB1 = DG(IB1,1) * (1.-DTB1) + DG(IB1+1,1) * DTB1 C FIND STOPPING DISTANCE FROM A VELOCITY OF VB1 TST1 = TS(IB1,1) * (1.-DTB1) + TS(IB1+1,1) * DTB1 DST1 = DS(IB1,1) * (1.-DTB1) + DS(IB1+1,1) * DTB1 C FIND TOTAL ACCELERATE-STOP DISTANCE - ALL ENGINES OPERATING DAS1 = DB1 + DST1 DAS = MAX( DAS1, DAS2 ) C FIND TAKEOFF DISTANCE - ONE ENGINE OUT 205 IRT = 1 + VROT / DELVTO IF ( IRT .GE. IRUN(2) ) IRT = IRUN(2) - 1 DTRT = 1. + VROT / DELVTO - IRT DRT2 = DG(IRT,2) * (1.-DTRT) + DG(IRT+1,2) * DTRT DROT = DRT2 - DDEF C IF NECESSARY, RECALCULATE ROTATION AND CLIMB TO OBSTACLE ICRIT = 2 IFAIL = 0 IF ( IREC .GT. 0 ) 1 CALL ROTCL ( VROT, GROSWT, DLO, TLO, VLO, ALLO, ILO, DOBST, 2 TOBST, VOBST, ALOST, GAOST, IOBST ) IF ( IFAIL .GT. 0 ) GO TO 400 DTO2 = DROT + DOBST IF ( IFITE .EQ. 1 ) DTO2 = DROT + DLO DELST = DAS - DTO2 IF ( ABS(DELST) .LT. .1 .OR. ITER .GT. 9 ) GO TO 230 DELV2 = - DELST * VEF / (DAS + DTO2) ITER = ITER + 1 IF ( ITER .GT. 1 ) GO TO 210 IF ( DELV2 .GT. 0. ) IREC = 1 GO TO 220 210 DELS = DELSO - DELST IF ( ABS(DELS) .GT. .01 ) DELV2 = DELST * (VEF - VOO) / DELS 220 VOO = VEF DELSO = DELST VEF = VEF + DELV2 IF ( IREC .EQ. 0 ) GO TO 140 IF ( IFITE .EQ. 0 ) THEN VROT = VEF + 5. * SPD ELSE VROT = VB2 ENDIF VEFR = VROT GO TO 140 C BALANCED FIELD LENGTH CALCULATIONS ARE COMPLETE - PRINT RESULTS 230 DBAL = (DAS + DTO2) / 2. IF ( IPRNT .LE. 0 ) GO TO 300 IF ( IFITE .EQ. 1 ) GO TO 255 C PRINT ALL-ENGINES-OPERATING ACCELERATE-STOP RESULTS DGV1 = DG(IV1,1) * (1.-DTV1) + DG(IV1+1,1) * DTV1 IF ( ITIME .EQ. 0 ) GO TO 240 C OUTPUT DETAILED PROFILE WRITE(IU6, 410) WRITE(IU6, 450) L = 1 WRITE(IU6, 460) (TG(I,L), DG(I,L), ZERO, VG(I,L)/SPD, 1 VG(I,L)/SPDSND, ZERO, ALPRUN, TINC, THG(I,L), 2 CGL(I,L), CGD(I,L), CGL(I,L)/CGD(I,L), ACG(I,L), 3 I = 1,IB1) THB1 = THG(IB1,1) * (1.-DTB1) + THG(IB1+1,1) * DTB1 CLB1 = CGL(IB1,1) * (1.-DTB1) + CGL(IB1+1,1) * DTB1 CDB1 = CGD(IB1,1) * (1.-DTB1) + CGD(IB1+1,1) * DTB1 ACB1 = ACG(IB1,1) * (1.-DTB1) + ACG(IB1+1,1) * DTB1 WRITE(IU6, 460) TB1, DB1, ZERO, VB1/SPD, VB1/SPDSND, ZERO, ALPRUN, 1 TINC, THB1, CLB1, CDB1, CLB1/CDB1, ACB1 WRITE(IU6, 470) J = IB1 + 1 WRITE(IU6, 460) (TB1+TST1-TS(J-I,L), DAS1-DS(J-I,L), ZERO, 1 VS(J-I,L)/SPD, VS(J-I,L)/SPDSND, ZERO, ALPRUN, 2 TINC, THS(J-I,L), CSL(J-I,L), CSD(J-I,L), 3 CSL(J-I,L)/CSD(J-I,L), ACS(J-I,L), I = 1,IB1) 240 WRITE(IU6, 250) V1/SPD, TB1-2., DGV1, VB1/SPD, TB1, DB1, ZERO, 1 TST1+TB1, DAS1 250 FORMAT (/' ACCELERATE - STOP DISTANCE',T33,'VELOCITY TIME', 1 T53,'DISTANCE',/' ALL ENGINES OPERATING',T35, 2 'KNOTS SEC. FEET',// 3 ' DECISION SPEED (V1)',T31,F10.2,F9.2,F11.2,/ 4 ' BRAKE APPLICATION (T1+2)',T31,F10.2,F9.2,F11.2,/ 5 ' COMPLETE STOP ',T31,F10.2,F9.2,F11.2 ) C PRINT ONE-ENGINE-OUT ACCELERATE-STOP RESULTS 255 TEF = TG(IEF,1) * (1.-DTEF) + TG(IEF+1,1) * DTEF TTEF = TG(IEF,2) * (1.-DTEF) + TG(IEF+1,2) * DTEF - TEF TV12 = TEF + PILOTT DGV2 = DG(IV1,2) * (1.-DTV1) + DG(IV1+1,2) * DTV1 - DDEF TB2 = TV12 + 2. IF ( ITIME .EQ. 0 ) GO TO 260 C OUTPUT DETAILED PROFILE WRITE(IU6, 420) WRITE(IU6, 450) L = 1 WRITE(IU6, 460) (TG(I,L), DG(I,L), ZERO, VG(I,L)/SPD, 1 VG(I,L)/SPDSND, ZERO, ALPRUN, TINC, THG(I,L), 2 CGL(I,L), CGD(I,L), CGL(I,L)/CGD(I,L), ACG(I,L), 3 I = 1,IEF) THEF = THG(IEF,1) * (1.-DTEF) + THG(IEF+1,1) * DTEF CLEF = CGL(IEF,1) * (1.-DTEF) + CGL(IEF+1,1) * DTEF CDEF = CGD(IEF,1) * (1.-DTEF) + CGD(IEF+1,1) * DTEF ACEF = ACG(IEF,1) * (1.-DTEF) + ACG(IEF+1,1) * DTEF WRITE(IU6, 460) TEF, DEF1, ZERO, VEF/SPD, VEF/SPDSND, ZERO, 1 ALPRUN, TINC, THEF, CLEF, CDEF, CLEF/CDEF, ACEF WRITE(IU6, 470) L = 2 J = IEF + 1 WRITE(IU6, 460) (TG(I,L)-TTEF, DG(I,L)-DDEF, ZERO, VG(I,L)/SPD, 1 VG(I,L)/SPDSND, ZERO, ALPRUN, TINC, THG(I,L), 2 CGL(I,L), CGD(I,L), CGL(I,L)/CGD(I,L), ACG(I,L), 3 I = J,IB2) THB2 = THG(IB2,2) * (1.-DTB2) + THG(IB2+1,2) * DTB2 CLB2 = CGL(IB2,2) * (1.-DTB2) + CGL(IB2+1,2) * DTB2 CDB2 = CGD(IB2,2) * (1.-DTB2) + CGD(IB2+1,2) * DTB2 ACB2 = ACG(IB2,2) * (1.-DTB2) + ACG(IB2+1,2) * DTB2 WRITE(IU6, 460) TB2, DB2, ZERO, VB2/SPD, VB2/SPDSND, ZERO, ALPRUN, 1 TINC, THB2, CLB2, CDB2, CLB2/CDB2, ACB2 WRITE(IU6, 470) J = IB2 + 1 WRITE(IU6, 460) (TB2+TST2-TS(J-I,L), DAS2-DS(J-I,L), ZERO, 1 VS(J-I,L)/SPD, VS(J-I,L)/SPDSND, ZERO, ALPRUN, 2 TINC, THS(J-I,L), CSL(J-I,L), CSD(J-I,L), 3 CSL(J-I,L)/CSD(J-I,L), ACS(J-I,L), I = 1,IB2) 260 WRITE(IU6, 270) VEF/SPD, TEF, DEF1 IF ( IFITE .EQ. 0 ) THEN WRITE(IU6, 271) V1/SPD, TV12, DGV2, 1 VB2/SPD, TB2, DB2, ZERO, TST2+TB2, DAS2 ELSE WRITE(IU6, 272) VB2/SPD, TB2, DB2, ZERO, TST2+TB2, DAS2 ENDIF 270 FORMAT (/' ACCELERATE - STOP DISTANCE',T33,'VELOCITY TIME', 1 T53,'DISTANCE',/' ONE ENGINE OUT (OEO)',T35, 2 'KNOTS SEC. FEET',// 3 ' ENGINE FAILURE (VEF)',T31,F10.2,F9.2,F11.2) 271 FORMAT (' DECISION SPEED (V1)',T31,F10.2,F9.2,F11.2,/ 1 ' BRAKE APPLICATION (T1+2)',T31,F10.2,F9.2,F11.2,/ 2 ' COMPLETE STOP ',T31,F10.2,F9.2,F11.2 ) 272 FORMAT (' BRAKE APPLICATION (TEF+3)',T31,F10.2,F9.2,F11.2,/ 2 ' COMPLETE STOP ',T31,F10.2,F9.2,F11.2 ) C PRINT ONE-ENGINE-OUT TAKEOFF RESULTS TROT = TG(IRT,2) * (1.-DTRT) + TG(IRT+1,2) * DTRT - TTEF IF ( ITIME .EQ. 0 ) GO TO 280 C OUTPUT DETAILED PROFILE WRITE(IU6, 430) WRITE(IU6, 450) L = 1 WRITE(IU6, 460) (TG(I,L), DG(I,L), ZERO, VG(I,L)/SPD, 1 VG(I,L)/SPDSND, ZERO, ALPRUN, TINC, THG(I,L), 2 CGL(I,L), CGD(I,L), CGL(I,L)/CGD(I,L), ACG(I,L), 3 I = 1,IEF) WRITE(IU6, 460) TEF, DEF1, ZERO, VEF/SPD, VEF/SPDSND, ZERO, 1 ALPRUN, TINC, THEF, CLEF, CDEF, CLEF/CDEF, ACEF WRITE(IU6, 470) L = 2 J = IEF + 1 WRITE(IU6, 460) (TG(I,L)-TTEF, DG(I,L)-DDEF, ZERO, VG(I,L)/SPD, 1 VG(I,L)/SPDSND, ZERO, ALPRUN, TINC, THG(I,L), 2 CGL(I,L), CGD(I,L), CGL(I,L)/CGD(I,L), ACG(I,L), 3 I = J,IRT) THRT = THG(IRT,2) * (1.-DTRT) + THG(IRT+1,2) * DTRT CLRT = CGL(IRT,2) * (1.-DTRT) + CGL(IRT+1,2) * DTRT CDRT = CGD(IRT,2) * (1.-DTRT) + CGD(IRT+1,2) * DTRT ACRT = ACG(IRT,2) * (1.-DTRT) + ACG(IRT+1,2) * DTRT WRITE(IU6, 460) TROT, DROT, ZERO, VROT/SPD, VROT/SPDSND, ZERO, 1 ALPRUN, TINC, THRT, CLRT, CDRT, CLRT/CDRT, ACRT WRITE(IU6, 470) WRITE(IU6, 460) (TR(I)+TROT, DR(I)+DROT, ZERO, VR(I)/SPD, 1 VR(I)/SPDSND, ZERO, ALR(I), TINC+ALR(I)-ALPRUN, 2 THR(I), CLR(I), CDR(I), CLR(I)/CDR(I), ACR(I), 3 I = 1,ILO) WRITE(IU6, 470) WRITE(IU6, 460) (T(I)+TROT, D(I)+DROT, ALT(I), V(I)/SPD, 1 V(I)/SPDSND, GAM(I), ALP(I), TINC+ALP(I)-ALPRUN, 2 TH(I), CLL(I), CDD(I), CLL(I)/CDD(I), ACL(I), 3 I = 1,IOBST) 280 WRITE(IU6, 290) VEF/SPD, TEF, DEF1, ALPRUN, ZERO, VROT/SPD, TROT, 1 DROT, ALPRUN, ZERO, VLO/SPD, TLO+TROT, DLO+DROT, 2 ALLO, ZERO, OBSTO, VOBST, TOBST+TROT, DOBST+DROT, 3 ALOST, GAOST 290 FORMAT (/' TAKEOFF DISTANCE',T33,'VELOCITY TIME',T53, 1 'DISTANCE ALPHA GAMMA',/' ONE ENGINE OUT (OEO)',T35, 2 'KNOTS SEC. FEET DEG. DEG.',// 3 ' ENGINE FAILURE (VEF)',T31,F10.2,F9.2,F11.2,2F9.2,/ 4 ' ROTATION SPEED (VR)',T31,F10.2,F9.2,F11.2,2F9.2,/ 5 ' LIFT OFF (VLOF)',T31,F10.2,F9.2,F11.2,2F9.2,/ 6 F8.0,' FOOT OBSTACLE ',T31,F10.2,F9.2,F11.2,2F9.2 ) C REDO SECOND SEGMENT CLIMB AND PRINT 300 V2 = VOBST * SPD VEE2 = VOBST THRU = XINT1( V2,VELTO,10,THRTO ) * (NE - 1) IF ( VROT .GT. SROT ) 1 CALL CLGRAD ( V2, RHOA, THRU, GROSWT, CG, SG, ALPTO, CLTO, CDTO, 1 ZERO, CDEOUT, ALPRUN, TINC, RAD, ALP2, FORCE2 ) IF ( IPRNT .EQ. 0 ) GO TO 310 AGAM2 = ATAN(GAM2) / RAD WRITE(IU6, 490) V2/SPD, ALP2, AGAM2, GAM2*100., FORCE2 IF ( FORCE2 .LT. 0.0 ) WRITE(IU6, 500) C DETERMINE TAKEOFF DISTANCE FOR ALL ENGINES OPERATING 310 IRA = 1 + VROT / DELVTO IF ( IRA .GE. IRUN(1) ) IRA = IRUN(1) - 1 DTRA = 1. + VROT / DELVTO - IRA DRTA = DG(IRA,1) * (1.-DTRA) + DG(IRA+1,1) * DTRA ICRIT = 1 CALL ROTCL ( VROT, GROSWT, DLO, TLO, VLO, ALLO, ILO, DOBST, TOBST, 1 VOBST, ALOST, GAOST, IOBST ) IF ( IFAIL .GT. 0 ) GO TO 400 DTOA = DRTA + DOBST C REQUIRED FIELD LENGTH IS THE GREATER OF 115 PERCENT OF THE C ALL-ENGINE TAKEOFF FIELD LENGTH AND THE BALANCED FIELD LENGTH FAROFF = FFCT * DTOA IF ( DBAL .GT. FAROFF ) FAROFF = DBAL IF ( IPRNT .EQ. 0 ) RETURN C PRINT ALL ENGINES OPERATING TAKEOFF RESULTS TROT = TG(IRA,1) * (1.-DTRA) + TG(IRA+1,1) * DTRA IF ( ITIME .EQ. 0 ) GO TO 320 C OUTPUT DETAILED PROFILE WRITE(IU6, 440) WRITE(IU6, 450) L = 1 WRITE(IU6, 460) (TG(I,L), DG(I,L), ZERO, VG(I,L)/SPD, 1 VG(I,L)/SPDSND, ZERO, ALPRUN, TINC, THG(I,L), 2 CGL(I,L), CGD(I,L), CGL(I,L)/CGD(I,L), ACG(I,L), 3 I = 1,IRA) THRT = THG(IRA,1) * (1.-DTRA) + THG(IRA+1,1) * DTRA CLRT = CGL(IRA,1) * (1.-DTRA) + CGL(IRA+1,1) * DTRA CDRT = CGD(IRA,1) * (1.-DTRA) + CGD(IRA+1,1) * DTRA ACRT = ACG(IRA,1) * (1.-DTRA) + ACG(IRA+1,1) * DTRA WRITE(IU6, 460) TROT, DRTA, ZERO, VROT/SPD, VROT/SPDSND, ZERO, 1 ALPRUN, TINC, THRT, CLRT, CDRT, CLRT/CDRT, ACRT WRITE(IU6, 470) WRITE(IU6, 460) (TR(I)+TROT, DR(I)+DRTA, ZERO, VR(I)/SPD, 1 VR(I)/SPDSND, ZERO, ALR(I), TINC+ALR(I)-ALPRUN, 2 THR(I), CLR(I), CDR(I), CLR(I)/CDR(I), ACR(I), 3 I = 1,ILO) WRITE(IU6, 470) WRITE(IU6, 460) (T(I)+TROT, D(I)+DRTA, ALT(I), V(I)/SPD, 1 V(I)/SPDSND, GAM(I), ALP(I), TINC+ALP(I)-ALPRUN, 2 TH(I), CLL(I), CDD(I), CLL(I)/CDD(I), ACL(I), 3 I = 1,IOBST) 320 WRITE(IU6, 330) VROT/SPD, TROT, DRTA, ALPRUN, ZERO, VLO/SPD, 1 TLO+TROT, DLO+DRTA, ALLO, ZERO, OBSTO, VOBST, 2 TOBST+TROT, DTOA, ALOST, GAOST IF ( IFITE .EQ. 0 ) WRITE(IU6, 335) IFCT, DTOA*FFCT 330 FORMAT (/' TAKEOFF DISTANCE',T33,'VELOCITY TIME',T53, 1 'DISTANCE ALPHA GAMMA',/' ALL ENGINES OPERATING (AEO)',T35, 2 'KNOTS SEC. FEET DEG. DEG.',// 3 ' ROTATION SPEED (VR)',T31,F10.2,F9.2,F11.2,2F9.2,/ 4 ' LIFT OFF (VLOF)',T31,F10.2,F9.2,F11.2,2F9.2,/ 5 F8.0,' FOOT OBSTACLE ',T31,F10.2,F9.2,F11.2,2F9.2) 335 FORMAT (/I8,' PERCENT OBSTACLE DISTANCE',T50,F11.2) VSF = 1.05 + .05*IFITE WRITE(IU6, 480) VSTALL, VSF, VSF*VSTALL, 1.2*VSTALL IF ( IFITE .EQ. 0 ) THEN WRITE(IU6, 340) VTR(1)/SPD IF ( VTR(2) .GT. 0. ) WRITE(IU6, 345) VTR(2)/SPD ELSE IF ( ILAG .EQ. 2 ) THEN WRITE(IU6, 350) VTR(1)/SPD IF ( VTR(2) .GT. 0. ) WRITE(IU6, 351) VTR(2)/SPD ELSE IF ( ILAG .EQ. 1 ) THEN WRITE(IU6, 355) VTR(1)/SPD IF ( VTR(2) .GT. 0. ) WRITE(IU6, 356) VTR(2)/SPD ELSE WRITE(IU6, 357) VTR(1)/SPD IF ( VTR(2) .GT. 0. ) WRITE(IU6, 358) VTR(2)/SPD ENDIF ENDIF IF ( VSTR .GT. 0. ) WRITE(IU6, 360) VSTR/SPD IF ( VSSR .GT. 0. ) WRITE(IU6, 370) VSSR/SPD IF ( VRM5 .GT. 0. ) WRITE(IU6, 380) VRM5/SPD IF ( VEFR .GT. 0. ) THEN IF ( IFITE .EQ. 0 ) THEN WRITE(IU6, 390) VEFR/SPD ELSE WRITE(IU6, 391) VEFR/SPD ENDIF ENDIF 340 FORMAT (' VLOF = 1.10*VMU (AEO) ',F10.2) 345 FORMAT (' VLOF = 1.05*VMU (OEO) ',F10.2) 350 FORMAT (' VLOF = 1.10*VSTALL (AEO) ',F10.2) 351 FORMAT (' VLOF = 1.10*VSTALL (OEO) ',F10.2) 355 FORMAT (' VLOF = POWER OFF VMU (AEO)',F9.2) 356 FORMAT (' VLOF = POWER OFF VMU (OEO)',F9.2) 357 FORMAT (' VLOF = .005 GRAD VEL (AEO)',F9.2) 358 FORMAT (' VLOF = .005 GRAD VEL (OEO)',F9.2) 360 FORMAT (' V2 = 1.20*VSTALL ',F10.2) 370 FORMAT (' SECOND SEGMENT CLIMB ',F10.2) 380 FORMAT (' TAKEOFF AT VR - 5 KNOTS ',F10.2) 390 FORMAT (' VEF + 5 KNOTS ',F10.2) 391 FORMAT (' TEF + 3 SECONDS ',F10.2) IF ( IFITE .EQ. 0 ) THEN WRITE(IU6, 395) FAROFF 395 FORMAT (/' FAR TAKEOFF FIELD LENGTH',T50,F11.2,' FEET' ) ELSE WRITE(IU6, 396) DTOA 396 FORMAT (/' DISTANCE TO OBSTACLE',T50,F11.2,' FEET' ) IF ( DBAL .GT. 0. ) WRITE(IU6, 397) DBAL 397 FORMAT (/' CRITICAL FIELD LENGTH',T50,F11.2,' FEET' ) ENDIF IF ( IFAIL .EQ. 0 ) RETURN 400 WRITE(IU6,2000) FAROFF = -1000000. RETURN 410 FORMAT (/' * * * ABORTED TAKEOFF - ALL ENGINES OPERATING * * *') 420 FORMAT (/' * * * ABORTED TAKEOFF - ONE ENGINE OUT * * *') 430 FORMAT (/' * * * ONE ENGINE OUT TAKEOFF * * *') 440 FORMAT (/' * * * ALL ENGINES OPERATING TAKEOFF * * *') 450 FORMAT (/2X,4HTIME,5X,8HDISTANCE,3X,8HALTITUDE,3X,8HVELOCITY,5X, 1 4HMACH,6X,5HCLIMB,4X,6HATTACK,5X,6HENGINE,5X,6HENGINE,5X,4HLIFT, 2 5X,4HDRAG,6X,3HL/D,4X,6HACCEL.,/45X,6HNUMBER,5X,5HANGLE,5X, 3 5HANGLE,4X,9HINCIDENCE,3X,6HTHRUST,4X,6HCOEFF.,3X,6HCOEFF.,4X, 4 5HRATIO,/8H SECONDS,5X,4HFEET,7X,4HFEET,7X,5HKNOTS,15X,7HDEGREES, 5 3X,7HDEGREES,4X,7HDEGREES,4X,6HPOUNDS,31X,6HFT/S/S,/) 460 FORMAT (1F7.2,3F11.2,1F11.4,1F10.3,1F10.3,1F11.3,1F12.1,2F9.4, 1 2F9.2) 470 FORMAT (' ') 480 FORMAT (/' STALL SPEED (VS)',T31,F10.2,/F9.2,' VS',T31,F10.2, 1 /' 1.20 VS',T31,F10.2, 2 //' ROTATION SPEED IN KNOTS REQUIRED TO MEET' ) 490 FORMAT (/' SECOND SEGMENT CLIMB',T31,F10.2,T61,2F9.2,// 1 ' FLIGHT PATH SLOPE = ',F8.2,' PERCENT' / 2 ' NET THRUST = ',F8.0,' POUNDS' ) 500 FORMAT (50H * * * FAILED SECOND SEGMENT CLIMB CRITERION * * * /) 510 FORMAT (/'1',/'# TAKEOFF PERFORMANCE RESULTS', 1 //32X,35HDRAG POLAR - GEAR DRAG NOT INCLUDED/) 520 FORMAT (5X,15HANGLE OF ATTACK,4X,10F10.2) 530 FORMAT (5X,16HLIFT COEFFICIENT,3X,10F10.4) 540 FORMAT (5X,16HDRAG COEFFICIENT,3X,10F10.4/) 545 FORMAT (5X,7HCDMTO =,1F7.4,9X,8HCDGEAR =,F7.4,9X,8HCDEOUT =, 1 F7.4,9X,7HCLTOM =,F7.4,8X,16HTAKEOFF WEIGHT =,F10.1,/) 550 FORMAT (32X,34HINPUT NET THRUST VALUES FOR ENGINE/) 560 FORMAT (5X,9HVELOCITY ,10F11.1) 570 FORMAT (5X,9HTHRUST ,10F11.1) 2000 FORMAT(30H * * * FAILED TAKEOFF * * * ) END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE GRRUN ( VEND, NE, GROSWT, CDG, CL, IRUN, CDEOUT ) C COMPUTES ACCELERATION GROUND RUN TABLES FOR USE IN TAKEOFF AND OUTPUT C VEND ENDING VELOCITY FOR TABLES C NE NUMBER OF ENGINES C GROSWT TAKEOFF GROSS WEIGHT C CDG DRAG COEFFICIENT C CL LIFT COEFFICIENT C IRUN(1) NUMBER OF ENTRIES IN TABLE - ALL ENGINES OPERATING C IRUN(2) NUMBER OF ENTRIES IN TABLE - ONE ENGINE OUT C CDEOUT ENGINE OUT DELTA DRAG COEFFICIENT IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO , CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON /SCRTCH/ TG(125,2), DG(125,2), VG(125,2), THG(125,2), 1 CGL(125,2), CGD(125,2), ACG(125,2), TS(125,2), 2 DS(125,2), VS(125,2), THS(125,2), CSL(125,2), 3 CSD(125,2), ACS(125,2), TR(250), DR(250), VR(250), 4 ALR(250), THR(250), CLR(250), CDR(250), ACR(250), 5 T(250), D(250), ALT(250), V(250), GAM(250), 6 ALP(250), TH(250), CLL(250), CDD(250), ACL(250), 7 KDUM(3200) COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD DIMENSION IRUN(2) DATA RAD /.0174533/ C CALCULATE PROFILE FROM START OF GROUND ROLL C UNTIL ROTATION SPEED IS REACHED G = 9.80665/.3048 I = 1 10 IM1 = I - 1 NEOP = NE - IM1 DELTAV = DELVTO IA = 1 VE = 0.0 DG(IA,I) = 0.0 TG(IA,I) = 0.0 VG(IA,I) = 0.0 CDP = XINT1( VE,VELTO,10,CDDP ) DCL = XINT1( VE,VELTO,10,CLDPOC ) / CL CGL(IA,I) = CL + DCL CGD(IA,I) = CDG + CDP + CDEOUT*IM1 STINC = NEOP * SIN( TINC * RAD ) CTINC = NEOP * COS( TINC * RAD ) C INITIAL THRUST AND ACCELERATION THRU = XINT1( VE,VELTO,10,THRTO ) THG(IA,I) = NEOP * THRU ACO = (THRU * CTINC - ROLLMU * GROSWT) * G / GROSWT ACG(IA,I) = ACO C INCREMENT VELOCITY UNTIL ROTATION SPEED IS REACHED 20 V1 = VG(IA,I) + DELTAV CDP = XINT1( V1,VELTO,10,CDDP ) DRAG = (CDG + CDP + CDEOUT*IM1) * V1 * V1 * RHOA THRU = XINT1( V1,VELTO,10,THRTO ) DCL = XINT1( V1,VELTO,10,CLDPOC ) / CL CLIFT = (CL + DCL) * RHOA * V1 * V1 + STINC * THRU ACC = (THRU * CTINC - DRAG - ROLLMU * (GROSWT - CLIFT)) * G / 1 GROSWT C TIME AND DISTANCE ARE CALCULATED FOR THE VELOCITY STEP DELT = 2.0 * DELTAV / (ACC + ACO) IA = IA + 1 IF ( IA .GT. 125 .OR. ACC .LT. 0.) GO TO 30 TG(IA,I) = TG(IA-1,I) + DELT DG(IA,I) = DG(IA-1,I) + DELT * 1 (VG(IA-1,I) + (2.0 * ACO + ACC) * DELT / 6.0) VG(IA,I) = V1 CGL(IA,I) = CL + DCL CGD(IA,I) = CDG + CDP + CDEOUT*IM1 THG(IA,I) = NEOP * THRU ACG(IA,I) = ACC IF ( V1 .GT. VEND .OR. CLIFT .GT. GROSWT ) GO TO 30 ACO = ACC GO TO 20 C LOOP BACK TO PICK UP ENGINE OUT TABLES IF APPROPRIATE 30 IRUN(I) = IA I = I + 1 IF ( I .EQ. 2 .AND. NE .GT. 1 .AND. IBAL .EQ. 1 ) GO TO 10 RETURN END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE CLGRAD ( V2, RHOA, THRU, GROSWT, CG, SG, ALPTO, CLTO, 1 CDTO, CDGEAR, CDEOUT, ALPRUN, TINC, RAD, ALP2, 2 FORCE2 ) C COMPUTE NET HORIZONTAL FORCE FOR EVALUATION OF CLIMB GRADIENT CRITERIA C V2 VELOCITY AT EVALUATION POINT C RHOA DENSITY * WING AREA / 2 C THRU THRUST AVAILABLE WITH ONE ENGINE OUT C GROSWT WEIGHT AT EVALUATION POINT C CG COSINE OF REQUIRED FLIGHT PATH ANGLE C SG SINE OF REQUIRED FLIGHT PATH ANGLE C ALPTO ANGLES OF ATTACK FOR AERODYNAMIC TABLES C CLTO LIFT COEFFICIENTS FOR AERODYNAMIC TABLES C CDTO DRAG COEFFICIENTS FOR AERODYNAMIC TABLES C CDGEAR LANDING GEAR DRAG COEFFICIENT C CDEOUT ENGINE OUT DELTA DRAG COEFFICIENT C ALPRUN ANGLE OF ATTACK ON GROUND C TINC THRUST INCIDENCE ON GROUND C RAD CONSTANT TO CONVERT DEGREES TO RADIANS C ALP2 ANGLE OF ATTACK - OUTPUT C FORCE2 NET FORCE - OUTPUT IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) DIMENSION ALPTO(10), CLTO(10), CDTO(10) RHV2 = V2 * V2 * RHOA CL = GROSWT * CG / RHV2 C ITERATE ON ANGLE OF ATTACK UNTIL NET VERTICAL FORCE = 0 M = 0 ALP2 = XINT1( CL,CLTO,10,ALPTO ) ALPO = ALP2 20 FORCV = RHV2 * XINT1(ALP2, ALPTO, 10, CLTO) - GROSWT * CG + THRU 1 * SIN((ALP2 - ALPRUN + TINC) * RAD) M = M + 1 IF ( ABS(FORCV) .LT. 0.0000001*GROSWT .OR. M .GT. 15 ) GO TO 40 IF ( M .GT. 1 ) GO TO 30 FORO = FORCV ALP2 = ALP2 - .1 GO TO 20 30 DELTLP = -FORCV * (ALP2 - ALPO) / (FORCV - FORO) ALPO = ALP2 FORO = FORCV ALP2 = ALP2 + DELTLP GO TO 20 C CALCULATE NET HORIZONTAL FORCE (FORCE2 = EXCESS THRUST) 40 FORCE2 = -RHV2 * (XINT1(ALP2, ALPTO, 10, CDTO) + CDGEAR + CDEOUT) 1 - GROSWT * SG + THRU * COS((ALP2 - ALPRUN + TINC) * RAD) RETURN END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE ROTCL ( VROT, GROSWT, DLO, TLO, VLO, ALLO, ILO, DOBST, 1 TOBST, VOBST, ALOST, GAOST, IOBST ) C DETERMINE INITIAL VALUE OF ROTATION SPEED BASED ON LIFTOFF SPEED C DETERMINE TAKEOFF PROFILE FOR ROTATION AND CLIMBOUT C VROT ROTATION SPEED C GROSWT TAKEOFF GROSS WEIGHT C DLO DISTANCE FROM START OF ROTATION TO LIFTOFF C TLO TIME FROM START OF ROTATION TO LIFTOFF C VLO LIFTOFF VELOCITY C ALLO LIFTOFF ANGLE OF ATTACK C ILO NUMBER OF POINTS IN ROTATION TABLES C DOBST DISTANCE FROM START OF ROTATION TO OBSTACLE C TOBST TIME FROM START OF ROTATION TO OBSTACLE C VOBST OBSTACLE VELOCITY C ALOST OBSTACLE ANGLE OF ATTACK C GAOST OBSTACLE FLIGHT PATH ANGLE C IOBST NUMBER OF POINTS IN CLIMBOUT TABLES C COMMON BLOCK ROTDAT C VTR ROTATION SPEED REQUIRED TO MEET LIFTOFF SPEEDS FOR C (1) ALL ENGINES OPERATING AND (2) ONE ENGINE OUT C ALFROT MAXIMUM ANGLE OF ATTACK ON THE GROUND C ALPMAX MAXIMUM ANGLE OF ATTACK DURING CLIMBOUT C CDGEAR LANDING GEAR DRAG COEFFICIENT C CDEOUT ENGINE OUT DELTA DRAG COEFFICIENT C SPAN WING SPAN C VSTALL STALL SPEED C V005 MAXIMUM OF 1.1 VSTALL AND SPEED REQUIRED FOR 0.5 PERCENT C CLIMB GRADIENT FOR FIGHTERS C NE NUMBER OF ENGINES C IFAIL FAILURE SWITCH C = 0, NORMAL C = 1, UNABLE TO TAKE OFF C ICRIT CRITICAL CONDITION INDICATOR C = 0, DETERMINE CRITICAL CONDITION C = 1, COMPUTE PROFILE FOR ALL ENGINES OPERATING C = 2, COMPUTE PROFILE FOR ONE ENGINE OUT C ILAG INDICATES WHICH IS CRITICAL FOR ROTATION SPEED C = 1, VLOF = POWER OFF VMU C = 2, VLOF = 1.1 VSTALL C = 3, VLOF = SPEED FOR .005 CLIMB GRADIENT IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /UNITS / IU5, IU6, IU7, IU8, IU9, IU16, IU17, IU18 COMMON / FORT / IFITE COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO , CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON /SCRTCH/ TG(125,2), DG(125,2), VG(125,2), THG(125,2), 1 CGL(125,2), CGD(125,2), ACG(125,2), TS(125,2), 2 DS(125,2), VS(125,2), THS(125,2), CSL(125,2), 3 CSD(125,2), ACS(125,2), TR(250), DR(250), VR(250), 4 ALR(250), THR(250), CLR(250), CDR(250), ACR(250), 5 T(250), D(250), ALT(250), V(250), GAM(250), 6 ALP(250), TH(250), CLL(250), CDD(250), ACL(250), 7 KDUM(3200) COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /ROTDAT/ VTR(2), ALFROT, ALPMAX, CDGEAR, CDEOUT, SPAN, 1 VSTALL, V005, NE, IFAIL, ICRIT, ILAG DIMENSION VIT(10), ALWR(10), HFOR(10), DELFOR(10) DATA G /32.174/, RAD /0.0174533/ C IS ROTATION VELOCITY (VROT) GIVEN OR TO BE FOUND SPD = 1852./(.3048*3600.) IM1 = ICRIT - 1 VMIN = VROT IF ( ICRIT .GT. 0 ) GO TO 30 C FIND VROT = MAX OF ROTATION SPEEDS WHICH PRODUCE LIFT OFF SPEEDS C FOR TRANSPORTS OF 1.10*VMU(1) OR 1.05*VMU(2) C WHERE 1 = ALL ENGINES OPERATING, 2 = ONE ENGINE OUT C FOR FIGHTERS, THE LIFT OFF SPEED IS THE MAXIMUM OF (1) POWER-OFF C VMU, (2) 1.1 VSTALL, AND (3) THE SPEED REQUIRED TO MAINTAIN A C CLIMB GRADIENT OF .005 WITH ONE ENGINE OUT I = 1 5 IM1 = I - 1 M = 1 DWO = 0. C CALCULATE VMU - ASSUME IT IS LIFTOFF SPEED AT ALPHA MAX ON GROUND ALPH1 = ALFROT DELTLP = ALPH1 - ALPRUN STHR = SIN( (TINC + DELTLP) * RAD ) V1 = 1.1 * VSTALL * SPD c ohad 16/7/08 - 0.0d0 rather than 0. c CALL GEFECT ( ALPH1, 0., 0., ALPTO, CLTO, CDTO, CDMTO, CL, CDG, c 1 ARRET*ARGEF, WHGT, SPAN ) CALL GEFECT ( ALPH1, 0.0d0, 0.0d0, ALPTO, CLTO, CDTO, CDMTO, CL, 1 CDG, ARRET*ARGEF, WHGT, SPAN ) C ITERATE TO FIND LIFTOFF VELOCITY 10 THRU = 0. IF ( IFITE .EQ. 0 ) THRU = XINT1( V1,VELTO,10,THRTO ) CLP = XINT1( V1,VELTO,10,CLDPOC ) DCL = CLP / CL VTHR = (NE - IM1) * STHR * THRU CLROS = (CL + DCL) * RHOA CLIFT = CLROS * V1 ** 2 + VTHR DELW = GROSWT - CLIFT IF ( ABS(DELW/GROSWT) .LT. .00001 .OR. M .GT. 10 ) GO TO 20 DELTAV = SQRT((GROSWT - VTHR)/CLROS) - V1 IF ( M .GT. 1 .AND. ABS(DELW-DWO) .GT. .0001 ) 1 DELTAV = DELW * (V1 - VO) / (DWO - DELW) IF ( ABS(DELTAV) .GT. V1/2. ) DELTAV = SIGN( V1/2., DELTAV) DWO = DELW VO = V1 V1 = V1 + DELTAV M = M + 1 GO TO 10 C CALCULATE PROFILE FROM START OF ROTATION UNTIL LIFTOFF 20 IF ( IFITE .EQ. 1 ) THEN IF ( V005 .LT. V1 ) THEN ILAG = 1 VTARG = V1 ELSE VTARG = V005 ENDIF ELSE VTARG = V1 * (1.15 - .05 * I) ENDIF V1O = 0. NV = 0 30 VE = VROT DE = 0. TI = 0. IA = 0 ALPOL = ALPRUN DELT = DELTRO ALPH1 = ALPRUN DELF = 1.0 ACO = 0.0 DACC = 0.0 IFIR = 1 IL = 0 IF ( ICRIT .GT. NE ) ICRIT = 1 GO TO 50 C ROTATE AT SPECIFIED RATE (VANGLE) AND C ESTIMATE VELOCITY AT THE END OF THE TIME STEP 40 DELTAL = VANGL * DELT ALPH1 = ALPH1 + DELTAL M = 0 50 DELTAV = DELT * (2.*ACO + DACC*DELT) / 2. IF ( ALPH1 .GT. ALFROT ) ALPH1 = ALFROT c ohad 16/7/08 - 0.0d0 rather than 0. c CALL GEFECT ( ALPH1,0.0,0.0,ALPTO,CLTO,CDTO,CDMTO,CL,CDG, c 1 ARRET*ARGEF,WHGT,SPAN ) CALL GEFECT ( ALPH1,0.0d0,0.0d0,ALPTO,CLTO,CDTO,CDMTO,CL,CDG, 1 ARRET*ARGEF,WHGT,SPAN ) C LOOP TO CONVERGE VELOCITY AT THE END OF THE TIME STEP C COMPUTE VERTICAL LIFT AND HORIZONTAL ACCELERATION 60 V1 = VE + DELTAV CDP = XINT1( V1,VELTO,10,CDDP ) DRAG = (CDG + CDGEAR + CDP + CDEOUT*IM1) * RHOA * V1 ** 2 THRU = XINT1( V1,VELTO,10,THRTO ) CLP = XINT1( V1,VELTO,10,CLDPOC ) DCL = CLP / CL DELTLP = ALPH1 - ALPRUN CLIFT = (CL + DCL) * RHOA * V1 ** 2 + (NE - IM1) * SIN( (TINC + 1 DELTLP) * RAD ) * THRU FRICT = ROLLMU * (GROSWT - CLIFT) IF ( FRICT .LT. 0.0 ) FRICT = 0.0 TNET = THRU * (NE - IM1) * COS( (TINC + DELTLP) * RAD ) FORC = TNET - DRAG - FRICT ACC = FORC * G / GROSWT IF ( ACC+ACO .LE. 0. ) THEN IFAIL = 2 RETURN ENDIF C IF THIS IS THE FIRST PASS FOR A NEW VROT, JUST ESTABLISH ACO IF ( IFIR .EQ. 0 ) GO TO 70 IFIR = 0 ACO = ACC GO TO 40 70 DVO = DELTAV IF ( DELT .GT. 0. ) DACC = (ACC - ACO) / DELT DELTAV = DELT * (ACO + ACC) / 2. IF ( IL .GT. 0 ) GO TO 80 M = M + 1 IF ( ABS(DELTAV-DVO) .GT. .001 .AND. M .LT. 10 ) GO TO 60 IF ( CLIFT .GT. GROSWT ) GO TO 80 TI = TI + DELT DE = DE + DELT * (VE + (2. * ACO + ACC) * DELT / 6.) VE = VE + DELTAV DELF = CLIFT - GROSWT ACO = ACC ALPOL = ALPH1 IA = IA + 1 IF ( IA .GT. 250 ) GO TO 340 TR(IA) = TI DR(IA) = DE VR(IA) = VE ALR(IA) = ALPH1 THR(IA) = THRU * (NE - IM1) CLR(IA) = CL + DCL CDR(IA) = CDG + CDGEAR + CDP + CDEOUT*IM1 ACR(IA) = ACC ILO = IA GO TO 40 C ITERATE UNTIL TIME OF LIFTOFF IS DETERMINED 80 IL = IL + 1 VIT(IL) = DELT DELFOR(IL) = CLIFT - GROSWT ALWR(IL) = ALPH1 HFOR(IL) = FORC C IF THE NET FORCE = 0, LIFTOFF HAS OCCURRED IF ( ABS( DELFOR(IL) ) .LT. 0.00001 * GROSWT ) GO TO 120 IF ( IL .GT. 1 ) GO TO 90 C FIRST ITERATION DELT = DELT * (1. - DELFOR(IL) / (DELFOR(IL) - DELF)) IF ( DELT .LT. 0.0 ) DELT = 0.0 GO TO 100 C SUBSEQUENT ITERATIONS - LINEAR INTERPOLATION 90 IF ( IL .GE. 10 ) GO TO 110 DELT = VIT(IL) - (VIT(IL) - VIT(IL-1)) * DELFOR(IL) / 1 (DELFOR(IL) - DELFOR(IL-1)) IF ( DELT .LE. 0.0 ) DELT = VIT(IL) / 2.0 IF ( DELT .LE. 0.0 ) GO TO 120 CHECK = DELFOR(IL)*DELFOR(IL-1) C TRY INTERVAL HALVING IF( IL.GT.5 .AND. CHECK.LT.0. ) DELT = (VIT(IL)+VIT(IL-1))/2.0 100 ALPH1 = ALPOL GO TO 40 110 IF ( ABS( VIT(IL) - VIT(IL-1) ) .LT. 0.001 ) GO TO 120 C NO CONVERGENCE - PRINT DIAGNOSTIC DATA WRITE(IU6, 350) (IL, VIT(IL), DELFOR(IL), ALWR(IL), HFOR(IL), 1 IL = 1,10) C LIFTOFF SPEED HAS BEEN FOUND, ITERATE TO MATCH TARGET 120 IF ( ICRIT .GT. 0 ) GO TO 140 NV = NV + 1 IF ( NV .EQ. 1 .AND. V1 .GE. VTARG ) GO TO 130 DELVR = V1 - VTARG IF ( ABS(DELVR) .LT. .001 .OR. NV .GT. 10 ) GO TO 130 DELV1 = V1 - V1O IF ( NV .GT. 1 .AND. ABS(DELV1) .GT. .001 ) 1 DELVR = (VROT-VRO) * DELVR / DELV1 VRO = VROT V1O = V1 VROT = VROT - DELVR GO TO 30 C ROTATION SPEED FOR THE TARGET LIFTOFF SPEED HAS BEEN FOUND 130 VTR(I) = VROT I = I + 1 IF ( I .LE. 2 .AND. NE .GT. 1 .AND. IBAL .EQ. 1 ) GO TO 5 ICRIT = 1 IF ( VTR(2) .GT. VTR(1) ) ICRIT = 2 VRCRIT = VTR(ICRIT) IF ( ICRIT .EQ. 2 .OR. NE .EQ. 1 .OR. IBAL .EQ. 0 ) GO TO 140 I = 2 IM1 = 1 VROT = VRCRIT IF ( VROT .LT. VMIN ) VROT = VMIN GO TO 30 140 DELTAV = (ACC + ACO) * DELT / 2.0 ALLO = ALPH1 TLO = TI + DELT DLO = DE + DELT * (VE + (2. * ACO + ACC) * DELT / 6.) VLO = VE + DELTAV ACO = ACC IA = IA + 1 IF ( IA .GT. 250 ) GO TO 340 TR(IA) = TLO DR(IA) = DLO VR(IA) = VLO ALR(IA) = ALPH1 THR(IA) = THRU * (NE - IM1) CLR(IA) = CL + DCL CDR(IA) = CDG + CDGEAR + CDP + CDEOUT*IM1 ACR(IA) = ACC ILO = IA C COMPUTE TRAJECTORY FROM LIFTOFF UNTIL OBSTACLE HEIGHT IS REACHED VVERT = 0.0 VHORZ = VLO TI = TLO IA = 0 DE = DLO GAMO = 0.0 DELO = 0.0 HOO = 0.0 ACHO = ACO ACVO = 0.0 DACV = 0.0 DGAM = 0.0 MAL = 0 IL = 0 HT = 0.0 DELT = DELTCL GAMFLT = 0.0 C INCREMENT TIME UNTIL ALTITUDE EXCEEDS OBSTACLE HEIGHT 230 DELTAV = DELT * (2.*ACO + DACC*DELT) / 2. IF ( DELTAV .LT. 0. ) DELTAV = 0. DELTAL = VANGL * DELT ALPOL = ALPH1 M = 0 C CONTINUE ROTATION LIMITED BY ALPMAX ALPH1 = ALPH1 + DELTAL 240 IF ( ALPH1 .GT. ALPMAX ) ALPH1 = ALPMAX GAMFLT = GAMO + DELT * DGAM DELTLP = ALPH1 - ALPRUN HO = HT + DELT * (VVERT + DELT * (3.*ACVO + DELT*DACV) / 6. ) CALL GEFECT ( ALPH1, HO, GAMFLT, ALPTO, CLTO, CDTO, CDMTO, CL, 1 CDG, ARRET*ARGEF, WHGT, SPAN ) V1 = VE + DELTAV C INCLUDE GEAR DRAG IF IT IS STILL DOWN CDGR = 0.0 IF ( (TI + DELT - TLO) .LE. TIGEAR .AND. TIGEAR .GT. 0. ) 1 CDGR = CDGEAR * COS(((TI+DELT-TLO) / TIGEAR) * 90. * RAD ) CDP = XINT1( V1,VELTO,10,CDDP ) DRAG = (CDG + CDGR + CDP + CDEOUT*IM1) * V1 ** 2 * RHOA CLP = XINT1(V1,VELTO,10,CLDPOC) DCL = CLP / CL CLIFT = (CL + DCL) * V1 ** 2 * RHOA THRU = XINT1( V1,VELTO,10,THRTO ) CG = COS( GAMFLT * RAD ) SG = SIN( GAMFLT * RAD ) TNETH = THRU * (NE - IM1) * COS( (TINC + DELTLP + GAMFLT) * RAD ) TNETV = THRU * (NE - IM1) * SIN( (TINC + DELTLP + GAMFLT) * RAD ) FORCH = TNETH - CLIFT * SG - DRAG * CG FORCV = TNETV + CLIFT * CG - GROSWT - DRAG * SG ACCH = FORCH * G / GROSWT ACCV = FORCV * G / GROSWT DACV = (ACCV - ACVO) / DELT HO = HT + DELT * (VVERT + DELT * (2.0 * ACVO + ACCV) / 6.0 ) TVERT = VVERT + DELT * (ACVO + ACCV) / 2.0 THORZ = VHORZ + DELT * (ACHO + ACCH) / 2.0 TV = SQRT(TVERT**2 + THORZ**2) GAMFLT = ATAN(TVERT / THORZ) / RAD DGAM = (GAMFLT - GAMO) / DELT ACC = (ACCH * THORZ + ACCV * TVERT ) / TV DELTAV = TV - VE M = M + 1 IF ( M .EQ. 1 ) GO TO 240 IF ( MAL .GT. 0 ) GO TO 280 IF ( ACC .GE. 0. ) GO TO 300 C IF FLIGHT PATH ACCELERATION IS NEGATIVE, REDUCE ALPHA C AND ITERATE UNTIL ACCELERATION IS ZERO DAL = -0.1 270 MAL = MAL + 1 ALPO = ALPH1 ACACO = ACC ALPH1 = ALPH1 + DAL DELTAV = DELT * ACO / 2. M = 0 GO TO 240 280 IF ( ABS(ACC) .GT. 0.001 .AND. MAL .LT. 10 .AND. ACC .NE. ACACO ) 1 GO TO 290 MAL = 0 GO TO 300 290 DAL = -ACC * (ALPH1 - ALPO) / (ACC - ACACO) GO TO 270 300 IF ( ABS(HO - OBSTO) .LT. 0.01 ) GO TO 320 IF ( IL .GT. 0 ) GO TO 310 IF ( HO .LT. OBSTO ) GO TO 330 C IF HEIGHT EXCEEDS OBSTACLE, ITERATE UNTIL EQUAL 310 DV = (DELT - DELO) * (HO - OBSTO) / (HO - HOO) DELO = DELT HOO = HO DELT = DELT - DV IF ( DELT .LT. 0.0 ) DELT = DELO / 2.0 IF ( DELT .GT. DELTCL ) DELT = (DELTCL + DELO) / 2.0 ALPH1 = ALPOL IL = IL + 1 IF ( IL .LT. 10 ) GO TO 230 320 IL = 10 330 CONTINUE HT = HO HOO = HT DE = DE + DELT * (VHORZ + (2.0 * ACHO + ACCH) * DELT / 6.0) VVERT = TVERT VHORZ = THORZ VE = TV GAMO = GAMFLT ACO = ACC ACHO = ACCH ACVO = ACCV TI = TI + DELT IA = IA + 1 IF ( IA .GT. 250 ) GO TO 340 T(IA) = TI D(IA) = DE V(IA) = VE ALP(IA) = ALPH1 TH(IA) = THRU * (NE - IM1) CLL(IA) = CL + DCL CDD(IA) = CDG + CDGR + CDP + CDEOUT*IM1 ALT(IA) = HT GAM(IA) = GAMFLT ACL(IA) = ACC IOBST = IA IF ( IL .LT. 10 ) GO TO 230 C FINISHED, OBSTACLE HAS BEEN REACHED 335 TOBST = TI VOBST = VE / SPD DOBST = DE ALOST = ALPH1 GAOST = GAMFLT RETURN 340 IFAIL = 1 IF ( ICRIT .EQ. 0 ) ICRIT = 2 GO TO 335 350 FORMAT (54H * * ITERATION OF LIFTOFF VELOCITY IS INCOMPLETE * */ 1(I5,6H DELT=,F7.3,8H DELFOR=,F10.2,7H ALPHA=,F7.3,6H HFOR=,F9.2)) END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE DECEL ( VEND, NE, GROSWT, CDG, CL, ISTP ) C COMPUTES DECELERATION GROUND RUN TABLES FOR ABORTED TAKEOFF AND OUTPUT C VEND ENDING VELOCITY FOR TABLES C NE NUMBER OF ENGINES C GROSWT TAKEOFF GROSS WEIGHT C CDG DRAG COEFFICIENT C CL LIFT COEFFICIENT C ISTP(1) NUMBER OF ENTRIES IN TABLE - ALL ENGINES OPERATING C ISTP(2) NUMBER OF ENTRIES IN TABLE - ONE ENGINE OUT IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO , CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON /SCRTCH/ TG(125,2), DG(125,2), VG(125,2), THG(125,2), 1 CGL(125,2), CGD(125,2), ACG(125,2), TS(125,2), 2 DS(125,2), VS(125,2), THS(125,2), CSL(125,2), 3 CSD(125,2), ACS(125,2), TR(250), DR(250), VR(250), 4 ALR(250), THR(250), CLR(250), CDR(250), ACR(250), 5 T(250), D(250), ALT(250), V(250), GAM(250), 6 ALP(250), TH(250), CLL(250), CDD(250), ACL(250), 7 KDUM(3200) COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /TREVRS/ RVFACT, TIRVRS, TIRVA, REVCUT, CLREV, CDREV, 1 VELRV(10), THRRV(10), INTHRV DIMENSION ISTP(2) DATA RAD /.0174533/ C CALCULATE PROFILE FROM STOP BACKWARDS TO BRAKE APPLICATION POINT G = 9.80665/.3048 I = 1 CLAB = CL + ISPOL * CLSPOL CDAB = CDG + ISPOL * CDSPOL 10 IM1 = I - 1 NEOP = NE - IM1 IAPRV = 0 DCLR = 0. DCDR = 0. VE = 0. THRU = XINT1( VE,VELLD,10,THRLD ) IF ( IREV-IM1 .GT. 0 ) THEN IAPRV = 1 IF ( REVCUT .LE. 0. ) THEN DCLR = CLREV DCDR = CDREV THRU = XINT1( VE,VELRV,10,THRRV ) * RVFACT ENDIF ENDIF DELTAV = DELVTO IA = 1 DS(IA,I) = 0.0 TS(IA,I) = 0.0 VS(IA,I) = 0.0 CSL(IA,I) = CLAB + DCLR CSD(IA,I) = CDAB + DCDR STINC = NEOP * SIN( TINC * RAD ) CTINC = NEOP * COS( TINC * RAD ) C FINAL THRUST AND ACCELERATION THS(IA,I) = NEOP * THRU ACO = - (THRU * CTINC - BRAKMU * GROSWT) * G / GROSWT ACS(IA,I) = - ACO C INCREMENT VELOCITY UNTIL DESIRED SPEED IS REACHED 20 V1 = VS(IA,I) + DELTAV THRU = XINT1( V1,VELLD,10,THRLD ) IF ( IAPRV .EQ. 1 .AND. (V1+DELTAV) .GE. REVCUT ) THEN CFACT = 1. IF ( V1 .LT. REVCUT ) CFACT = (V1 + DELTAV - REVCUT)/DELTAV THRU = XINT1(V1,VELRV,10,THRRV)*RVFACT*CFACT + THRU*(1.-CFACT) DCLR = CLREV * CFACT DCDR = CDREV * CFACT ENDIF CLIFT = (CLAB+DCLR) * V1*V1*RHOA + STINC*THRU DRAG = (CDAB+DCDR) * V1*V1*RHOA ACC = - (THRU*CTINC - DRAG - BRAKMU*(GROSWT-CLIFT)) * G/GROSWT C TIME AND DISTANCE ARE CALCULATED FOR THE VELOCITY STEP DELT = 2.0 * DELTAV / (ACC + ACO) IA = IA + 1 IF ( IA .GT. 125 .OR. ACC .LT. 0.) GO TO 30 TS(IA,I) = TS(IA-1,I) + DELT DS(IA,I) = DS(IA-1,I) + DELT * 1 (VS(IA-1,I) + (2.0 * ACO + ACC) * DELT / 6.0) VS(IA,I) = V1 CSL(IA,I) = CLAB CSD(IA,I) = CDAB THS(IA,I) = NEOP * THRU ACS(IA,I) = - ACC IF ( V1 .GT. VEND .OR. CLIFT .GT. GROSWT ) GO TO 30 ACO = ACC GO TO 20 C LOOP BACK TO PICK UP ENGINE OUT TABLES IF APPROPRIATE 30 ISTP(I) = IA I = I + 1 IF ( I .EQ. 2 .AND. NE .GT. 1 .AND. IBAL .EQ. 1 ) GO TO 10 RETURN END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE GEFECT ( ALPHA, H, GAM, ATB, CLT, CDT, CDM, CL, CDG, 1 AR, WHGT, SPAN ) C IMPLEMENTATION OF THE JOHN DEYOUNG GROUND EFFECTS EQUATIONS C ALPHA = ANGLE OF ATTACK C H = ALTITUDE C GAM = FLIGHT PATH ANGLE C ATB = ANGLE OF ATTACK TABLES C CLT = LIFT COEFFICIENT TABLES C CDT = DRAG COEFFICIENT TABLES C CDM = MINIMUM DRAG COEFFICIENT C CL = LIFT COEFFICIENT IN GROUND EFFECT C CDG = DRAG COEFFICIENT IN GROUND EFFECT C AR = WING ASPECT RATIO C WHGT = WING HEIGHT ABOVE GROUND AT ZERO ALTITUDE C SPAN = WING SPAN IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /GEFSW / INCGEF DIMENSION ATB(10),CLT(10),CDT(10) CL = XINT1( ALPHA,ATB,10,CLT ) CDG = XINT1( ALPHA,ATB,10,CDT ) IF ( INCGEF .LE. 0 ) RETURN HF = (H + WHGT) / SPAN C CHECK FOR OUT OF GROUND EFFECT IF ( HF .GE. 1.1 ) RETURN C 10 PERCENT RAMP TO PREVENT DISCONTINUITY IN GROUND EFFECTS HFACT = 1.0 IF ( HF .GT. 1.0 ) HFACT = 10. * (1.1 - HF) C PREVENT RIDICULOUS VALUES IF HF IS NEGATIVE IF (HF .LT. 0.0) HF = 0.0 A = (6 + AR) ** 2 / (36.0 + AR) B = 32.0 * (HF * A) ** 2 + 1.0 D = (ALPHA + GAM) * 0.0174533 DENOM = B - 0.5 + 4.0 * HF * A * SQRT(B) CLFACT = 1.0 + HFACT / DENOM B = 1. + 32.0 * HF ** 2 DENOM = 4.0 * HF * SQRT(B) + B PHII = 1.0 - HFACT / DENOM CDG = CDM + CLFACT * PHII * (CDG-CDM) + D * CL * (CLFACT-1.) CL = CL * CLFACT RETURN END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE LNDING ( FDLNGT, GROSWT, IFLAG, ARN, SW, GLOV, 1 NENG, FORCE2, APRVEL ) C EVALUATE ENGINE-OUT MISSED APPROACH CLIMB GRADIENT CONSTRAINT C COMPUTE LANDING PROFILE AND FIELD LENGTH C FDLNGT = LANDING FIELD LENGTH C GROSWT = LANDING GROSS WEIGHT C IFLAG = PRINT SWITCH C ARN,SW,GLOV = CURRENT ASPECT RATIO, WING AREA, AND GLOVE AREA C NENG = NUMBER OF ENGINES C FORCE2 = THRUST SURPLUS AFTER MEETING MISSED APPROACH CLIMB C GRADIENT (IF NEGATIVE, DELTA THRUST REQUIRED) C APRVEL = APPROACH VELOCITY - OUTPUT IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /UNITS / IU5, IU6, IU7, IU8, IU9, IU16, IU17, IU18 COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO, CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON / LAND / ALMXLD,APRANG,CLLDM ,TISPOL,TIBRAK,CDMW ,DMO , 1 ACCLIM,DELTRN,OBSLD ,DELHAP,DELDFL,CDMLD ,APRHGT, 2 SWING, AR, THDRY, CLLD(10), CDLD(10), ALPLD(10), 3 MAGRUP COMMON /SCRTCH/ T(300), D(300), ALT(300), V(300), EM(300), 1 GAM(300), ALP(300), TANG(300), TH(300), CLL(300), 2 CDD(300), ELOD(300), ACN(10), ALPHE(10), 3 DELFOR(10), H(10), HLAND(10), VIT(10), ALWR(10), 4 HFOR(10), SDUM(4320), KDUM(3200) COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /TREVRS/ RVFACT, TIRVRS, TIRVA, REVCUT, CLREV, CDREV, 1 VELRV(10), THRRV(10), INTHRV COMMON /OBSDAT/ VOBST, AOBST, THOBST COMMON / FORT / IFITE C SCALE AERODYNAMIC DRAG ASSUMING PARABOLIC POLAR C INITIALIZE CONSTANTS AND CONFIGURATION DATA SPAN = SQRT(ARN * (SW - GLOV)) CDM = CDMW + DMO / SW ZERO = 0. DO 1 I = 1,10 CDLD(I) = (CDLD(I) - CDMLD) * AR / ARN + CDM 1 CONTINUE CDGEAR = CDGRO / SW CDEOUT = CDEOT / SW CDMLD = CDM SWING = SW AR = ARN FARFCT = 0.6 + 0.4*IFITE G = 32.174 FTOL = -.000001*GROSWT ISTOP = 0 ALPMIN = ALPLD(1) - 3.0 CUTBK = 1.0 THM1 = 0.0 TIBR = TIBRAK TISP = TISPOL TIRV = TIRVRS RAD = 0.0174533 SPD = 1852. / 0.3048 / 3600.0 NE = NENG CLMAX = CLLDM ALCLM = XINT1( CLMAX/1.69, CLLD, 10, ALPLD ) IF ( ALCLM .GT. ALMXLD ) 1 CLMAX = 1.69 * XINT1 ( ALMXLD, ALPLD, 10, CLLD ) C PRINT CURRENT DRAG POLAR AND THRUST SCHEDULES IF ( IFLAG .LE. 0 ) GO TO 10 IF ( IFLAG .NE. 5 ) WRITE(IU6, 5) 5 FORMAT ('1') WRITE(IU6, 610) WRITE(IU6, 430) WRITE(IU6, 440) (ALPLD(I), I = 1,10) WRITE(IU6, 450) (CLLD(I), I = 1,10) WRITE(IU6, 460) (CDLD(I), I = 1,10) WRITE(IU6, 470) CDMLD, CDGEAR, CDEOUT, CLLDM, GROSWT IF ( CLMAX .LT. CLLDM ) WRITE(IU6,475 ) CLMAX, ALMXLD WRITE(IU6, 480) WRITE(IU6, 500) (VELLD(I), I = 1,10) WRITE(IU6, 510) (THRLD(I), I = 1,10) IF ( RVFACT .EQ. 0.0 ) GO TO 10 WRITE(IU6, 490) WRITE(IU6, 500) (VELRV(I), I = 1,10) WRITE(IU6, 510) (THRRV(I), I = 1,10) 10 RHOA = ANS1 * SWING / 2.0 VSTALL = SQRT( GROSWT / (CLMAX * RHOA) ) / SPD APRVEL = (1.3 - .1*IFITE) * VSTALL V2 = APRVEL * SPD C CALCULATE VMU - ASSUME IT IS LIFTOFF SPEED AT ALPHA MAX ON GROUND C CONSTRAIN HORIZONTAL SPEED UNTIL TOUCHDOWN TO BE .GE. 1.05 VMU ALPH1 = ALMXLD DELTLP = ALPH1 - ALPRUN STHR = SIN( (TINC + DELTLP) * RAD ) CGAM = COS( APRANG * RAD ) VMUM = 1.1 * VSTALL * SPD VMU = VMUM DWO = 0.0 M = 1 c ohad 16/7/08 - 0.0d0 rather than 0. c CALL GEFECT ( ALPH1, 0., 0., ALPLD, CLLD, CDLD, CDMLD, CL, CDG, c 1 AR*ARGEF, WHGT, SPAN ) CALL GEFECT ( ALPH1, 0.0d0, 0.0d0, ALPLD, CLLD, CDLD, CDMLD, CL, 1 CDG, AR*ARGEF, WHGT, SPAN ) C ITERATE TO FIND LIFTOFF VELOCITY 15 THRU = XINT1( VMU, VELLD, 10, THRLD ) IF ( IFITE .EQ. 1 .AND. THRU .GT. 0. ) THRU = 0. VTHR = NE * STHR * THRU CLROS = CL * RHOA CLIFT = CLROS * VMU ** 2 + VTHR DELW = GROSWT - CLIFT IF ( ABS(DELW/GROSWT) .LT. .00001 .OR. M .GT. 10 ) GO TO 17 DELTAV = SQRT((GROSWT - VTHR)/CLROS) - VMU IF ( M .GT. 1 .AND. ABS(DELW-DWO) .GT. .0001 ) 1 DELTAV = DELW * (VMU - VMO) / (DWO - DELW) DWO = DELW VMO = VMU VMU = VMU + DELTAV M = M + 1 GO TO 15 17 IF ( IFITE .EQ. 1 ) THEN IF ( VMU .LT. VMUM ) VMU = VMUM ELSE VMU = 1.05 * VMU ENDIF IF ( V2 .LT. VMU/CGAM ) V2 = VMU/CGAM C MISSED APPROACH CLIMB GRADIENT CALCULATIONS - ONE ENGINE OUT IF ( NE .EQ. 1 ) GO TO 50 C CALCULATE REQUIRED CLIMB GRADIENT GAM2 = ATAN( 0.015 + 0.003 * NE ) IF ( IFITE .EQ. 1 ) GAM2 = 0.025 SG = SIN ( GAM2 ) CG = COS ( GAM2 ) IRR = 0 C DETERMINE NET THRUST IF CLIMB GRADIENT IS MET 20 NEOP = NE - 1 IF ( NE .EQ. 1 ) NEOP = 1 CDGR = CDGEAR IF ( MAGRUP .EQ. 1 ) CDGR = 0. IF ( IFITE .EQ. 1 .AND. THDRY .GT. 0. ) THEN THRU = THDRY * NEOP ELSE THRU = XINT1( V2,VELTO,10,THRTO ) * NEOP ENDIF CALL CLGRAD ( V2, RHOA, THRU, GROSWT, CG, SG, ALPLD, CLLD, CDLD, 1 CDGR, CDEOUT, ALPRUN, TINC, RAD, ALP2, FORCE2 ) IF ( IRR .GT. 1 ) GO TO 30 IF ( FORCE2 .GE. FTOL ) GO TO 50 C MISSED APPROACH CLIMB GRADIENT CRITERION FAILED C INCREASE V2 UNTIL CRITERION IS MET C FIRST ITERATION IRR = 2 VO = V2 FORO = FORCE2 V2 = 1.05 * V2 GO TO 20 C SUBSEQUENT ITERATIONS 30 IRR = IRR + 1 IF ( ABS(FORCE2) .LE. -FTOL .OR. IRR .GT. 10 ) GO TO 40 DELV = (V2 - VO) * FORCE2 / (FORO - FORCE2) IF ( ABS(DELV) .GT. .1*V2 ) DELV = SIGN( .1*V2, DELV) C IF DIRECTION IS WRONG, HALVE INTERVAL IF ( DELV*FORCE2 .LT. 0. ) GO TO 35 V2 = (VO + V2) / 2. GO TO 20 35 VO = V2 FORO = FORCE2 V2 = V2 + DELV GO TO 20 40 IF ( FORCE2 .GE. FTOL .OR. (V2-.001) .LE. APRVEL*SPD ) 1 GO TO 50 V2 = APRVEL * SPD GO TO 20 C DETERMINE LANDING PROFILE 50 DELTLP = TINC - ALPRUN HSTOP = 100.0 GAMFLT = -APRANG SGAM = SIN( GAMFLT * RAD ) TGAM = TAN( GAMFLT * RAD ) IA = 1 I = 1 HT = APRHGT CDGR = CDGEAR TI = 0.0 DE = 0.0 APRVEL = V2 / SPD VE = V2 C BEGIN ITERATION ON START OF FLARE ALTITUDE C ITERATE UNTIL SOFT LANDING IS ACHIEVED 60 RHOS = RHOA * VE * VE CL = GROSWT / RHOS ALPH1 = XINT1( CL,CLLD,10,ALPLD ) IF ( ALPH1 .GT. ALMXLD ) ALPH1 = ALMXLD DELD = DELHAP/ TGAM DELT = DELHAP/ SGAM / VE C START POINT FOR NEW (INTERMEDIATE) ALTITUDES 70 HNEW = HT - DELHAP IF ( HNEW .GT. HSTOP ) GO TO 80 HNEW = HSTOP DELT = (HT - HSTOP) / SGAM / VE DELD = (HT - HNEW) / TGAM 80 TI = TI + DELT DE = DE + DELD ALPHE(1) = ALPH1 K = 1 C START LOOP TO DETERMINE EQUILIBRIUM CONDITIONS - FIND ANGLE OF C ATTACK AND THRUST REQUIRED FOR APPROACH SPEED AND GLIDE SLOPE 90 CALL GEFECT ( ALPHE(K), HNEW, -GAMFLT, ALPLD, CLLD, CDLD, CDMLD, 1 CL, CDG, AR*ARGEF, WHGT, SPAN ) CLIFT = CL * RHOS DRAG = (CDG + CDGR) * RHOS ALPNU = (ALPHE(K) + DELTLP) * RAD FH = DRAG - GROSWT * SGAM FORCH = FH / COS(ALPNU) FV = GROSWT * CGAM - CLIFT FORCV = FV / SIN(ALPNU) DELFOR(K) = FORCH - FORCV C ITERATE ON ALPHA UNTIL THE REQUIRED FORCE PERPENDICULAR TO C THE THRUST VECTOR = 0 IF ( ABS(DELFOR(K)) .LT. 0.00001 * GROSWT ) GO TO 120 IF ( K .GT. 1 ) GO TO 100 C FIRST ITERATION K = K + 1 ALPHE(K) = ALPHE(K - 1) - .1 GO TO 90 C SUBSEQUENT ITERATIONS 100 IF ( K .EQ. 10 ) GO TO 110 DALPHE = (ALPHE(K)-ALPHE(K-1))/(DELFOR(K)-DELFOR(K-1)) * DELFOR(K) IF(K.GE.3)DALPHE = DALPHE*(1. - DALPHE/(ALPHE(K)-ALPHE(K-1))/2.0) K = K + 1 ALPHE(K) = ALPHE(K - 1) - DALPHE IF(ALPHE(K).LT.ALPMIN.AND.ALPHE(K-1).GT.ALPMIN) ALPHE(K) = ALPMIN IF(ALPHE(K).GT.ALMXLD.AND.ALPHE(K-1).LT.ALMXLD) ALPHE(K) = ALMXLD GO TO 90 C NO CONVERGENCE - PRINT DIAGNOSTIC DATA 110 WRITE(IU6, 530) WRITE(IU6, 540) (K, ALPHE(K), K, DELFOR(K), K = 1,10) C CALCULATE THRUST REQUIRED TO MAINTAIN GLIDE SLOPE 120 THRU = (FORCH + FORCV) / (2.0 * NE) ALPH1 = ALPHE(K) IF ( TI .LT. IA .AND. I .GT. 1 ) GO TO 130 C FILL OUTPUT TABLES AT ONE SECOND INTERVALS CDD(I) = CDG + CDGR CLL(I) = CL V(I) = VE / SPD T(I) = TI D(I) = DE TANG(I) = ALPH1 + DELTLP ALP(I) = ALPH1 ALT(I) = HNEW TH(I) = THRU * NE GAM(I) = -GAMFLT EM(I) = VE / SPDSND ELOD(I) = 0.0 IF ( I .GT. 1 ) IA = IA + 1 I = I + 1 130 HT = HNEW IF ( HNEW .NE. HSTOP ) GO TO 70 IF ( HNEW .NE. 100.0 ) GO TO 140 C FIRST PLATEAU, H = 100., HAS BEEN REACHED MCUT = 1 HST = 100.0 DST = DE TST = TI FDLIM = 2.*(HST/TGAM) + DST ALPHST = ALPH1 GAMST = GAMFLT VST = VE H(MCUT) = OBSLD / 2. GO TO 260 C SECOND PLATEAU, START OF FLARE, HAS BEEN REACHED 140 CONTINUE DFLAR = DE TFLAR = TI HFLAR = HNEW ALPFLR = ALPH1 VFLAR = VE FLDMAX = 0.25 * G FLDMX1 = FLDMAX FLDMX2 = 1.0 LAN = 1 DELT = DELDFL / VST THMAX = THRU C COMPUTE TRAJECTORY FROM START OF FLARE TO LANDING VVERT = VE * SGAM VHORZ = VE * CGAM IANG = 1 IGAM = 1 LIMV = 0 ACCH = 0.0 ACCV = 0.0 ACVO = 0.0 ACHO = 0.0 ACVE = 0.0 ACHE = 0.0 SANO = SGAM C BEGIN FLARE STEP - NOTE VERTICAL ACCELERATION IS POSITIVE UP C VERTICAL VELOCITY IS POSITIVE DOWN 150 VVO = VVERT - (DELT * ACVE + 2.0 * ACVO) * DELT / 2.0 IF ( VVO .GT. VVERT ) VVO = VVERT IF ( DELT .LT. 0.1 * DELDFL / VST ) GO TO 160 IF ( VVO .GE. 0.0 ) GO TO 160 C IF VERTICAL VELOCITY IS NEGATIVE, FIND NADIR VVO = 0.0 DELTA = VVERT / ACVO IF ( ACVE .NE. 0.0 ) 1 DELTA = (SQRT( ACVO**2 + 2.0 * ACVE * VVERT ) - ACVO) / ACVE IF ( DELT .GT. DELTA ) DELT = DELTA 160 VHO = VHORZ - (DELT * ACHE + 2.0 * ACHO) * DELT / 2.0 IF ( VHO .GE. VMU ) GO TO 165 VHO = VMU LIMV = 1 165 VO = SQRT(VVO * VVO + VHO * VHO) SANGLE = VVO / VO IF ( SANGLE .GT. SANO ) SANGLE = SANO SANO = SANGLE CANGLE = SQRT(1. - SANGLE*SANGLE) GAMFLT = ASIN(SANGLE) / RAD M = 1 H1 = HT - (VVERT - (3. * ACVO + DELT * ACVE) * DELT / 6.) * DELT RHOS = RHOA * VO * VO C GRADUALLY REDUCE THRUST PROPORTIONAL TO FLIGHT PATH ANGLE THNU = XINT1( VO,VELLD,10,THRLD ) THRU = THNU + (THMAX - THNU) * SANGLE / SGAM C ONCE ALPHA HAS BEEN CONSTRAINED, GRADUALLY REDUCE MAXIMUM C VERTICAL ACCELERATION FOR SMOOTH TRANSITION IF(IGAM.NE.1) FLDMAX = FLDMX2 + (FLDMX1-FLDMX2) / GAMMAX * GAMFLT ALPOLD = ALPH1 IF ( IANG .GT. 1 ) GO TO 170 C CONTINUE FLARE ROTATION ALPH1 = ALPH1 + VANGL * DELT IF ( ALPH1 .LE. ALMXLD ) GO TO 170 C ALPHA CONSTRAINED BY ALMXLD ALPH1 = ALMXLD IANG = 2 170 CALL GEFECT ( ALPH1, H1, -GAMFLT, ALPLD, CLLD, CDLD, CDMLD, CL, 1 CDG, AR*ARGEF, WHGT, SPAN ) DRAG = (CDG + CDGR) * RHOS CLIFT = CL * RHOS TFCT = NE * SIN( (ALPH1 + DELTLP - GAMFLT) * RAD ) TFCC = SQRT(NE*NE - TFCT*TFCT) 172 FORCV = CLIFT * CANGLE + DRAG * SANGLE - GROSWT + THRU * TFCT IF ( FORCV .GE. 0. ) GO TO 173 FORCV = 0. THRU = ( GROSWT - DRAG * SANGLE - CLIFT * CANGLE ) / TFCT 173 FORCH = DRAG * CANGLE - CLIFT * SANGLE - THRU * TFCC IF ( FORCH .GE. -.1 .OR. LIMV .EQ. 0 ) GO TO 175 FORCH = 0. THRU = ( DRAG * CANGLE - CLIFT * SANGLE ) / TFCC GO TO 172 175 ACCV = FORCV * G / GROSWT IF ( ACCV .LT. FLDMAX .AND. M .EQ. 1 ) GO TO 200 C ALPHA IS CONSTRAINED BY NORMAL ACCELERATION LIMIT C ITERATE ON ALPHA TO GET MAXIMUM VALUE AT MAXIMUM NORMAL ACCEL. ACN(M) = ACCV - FLDMAX IANG = 2 IF ( ABS(ACN(M)) .LT. 0.001 .AND. ACCV .GE. 0.0 ) GO TO 200 ALPHE(M) = ALPH1 M = M + 1 IF ( M .GT. 2 ) GO TO 180 C FIRST ITERATION - SET ANGLE EQUAL TO MINIMUM ALLOWABLE ANGLE ALPH1 = ALPOLD - VANGL * DELT GO TO 170 C SUBSEQUENT ITERATIONS 180 IF ( M .GT. 10 ) GO TO 190 IF ( ACCV .GT. FLDMAX .AND. M .EQ. 3 ) GO TO 200 IF ( ACCV .LT. FLDMAX .AND. ALPH1 .GE. ALMXLD ) GO TO 200 ALPH1 = ALPHE(M-1) - (ALPHE(M-1) - ALPHE(M-2)) / 1 (ACN(M-1) - ACN(M-2)) * ACN(M-1) IF ( ALPH1 .GT. ALMXLD ) ALPH1 = ALMXLD GO TO 170 C NO CONVERGENCE - PRINT DIAGNOSTIC DATA 190 WRITE(IU6, 550) WRITE(IU6, 560) (M, ALPHE(M), M, ACN(M), M = 1,10) 200 ACCH = FORCH * G / GROSWT DELV = (ACCV + ACVO) * DELT / 2.0 IF (((VVERT-DELV).GT.-0.00001) .AND. (DELT.GT.0.001)) GO TO 210 C IF VELOCITY PROJECTS PAST ZERO, TRY TO HIT ZERO DELV = VVERT DELT = 2.0 * VVERT / (ACCV + ACVO) LAN = LAN + 1 C LAN > 1 INDICATES VERTICAL VELOCITY HAS REACHED ZERO 210 HT = HT - DELT * (VVERT - (2.0 * ACVO + ACCV) * DELT / 6.0) DE = DE + DELT * (VHORZ - (2.0 * ACHO + ACCH) * DELT / 6.0) VVERT = VVERT - DELV VHORZ = VHORZ - (ACCH + ACHO) * DELT / 2.0 IF ( VHORZ .LT. VMU ) VHORZ = VMU IF ( IGAM .GT. 1 .OR. IANG .EQ. 1 ) GO TO 220 C IF ALPHA IS CONSTRAINED, SET UP FOR ACCELERATION LIMIT VE = SQRT(VHORZ * VHORZ + VVERT * VVERT) GAMMAX = VVERT / VE / RAD IGAM = 2 220 ACVE = (ACCV - ACVO) / DELT ACHE = (ACCH - ACHO) / DELT ACVO = ACCV ACHO = ACCH IF ( IANG .LT. 2 ) ALPH1 = ALPOLD + VANGL * DELT TI = TI + DELT C FILL OUTPUT TABLES AT ONE SECOND INTERVALS IF ( TI .LT. IA ) GO TO 230 VE = SQRT( VHORZ * VHORZ + VVERT * VVERT ) CDD(I) = CDG + CDGR CLL(I) = CL V(I) = VE / SPD T(I) = TI D(I) = DE TANG(I) = ALPH1 + DELTLP ALP(I) = ALPH1 ALT(I) = HT TH(I) = THRU * NE GAM(I) = -VVERT / VE / RAD EM(I) = VE / SPDSND ELOD(I) = SQRT(ACCV * ACCV + ACCH * ACCH) IA = IA + 1 I = I + 1 230 IF ( LAN .LT. 2 .AND. DE .LT. FDLIM ) GO TO 150 VE = VHORZ C ITERATE ON FLARE ALTITUDE UNTIL ALTITUDE IS 0 AT END OF FLARE IF ( ABS(HT) .LT. 0.2 ) GO TO 270 H(MCUT) = HSTOP HLAND(MCUT) = HT MCUT = MCUT + 1 IF ( MCUT .GT. 2 ) GO TO 240 C FIRST ITERATION H(MCUT) = H(MCUT-1) - HLAND(MCUT-1) * 1.25 GO TO 260 C SUBSEQUENT ITERATIONS 240 IF ( MCUT .GT. 10 ) GO TO 250 DHM = HLAND(MCUT-1) - HLAND(MCUT-2) H(MCUT) = H(MCUT-1) - 5. IF ( ABS(DHM) .GE. .1 ) H(MCUT) = H(MCUT-1) 1 - (H(MCUT-1) - H(MCUT-2)) / DHM * HLAND(MCUT-1) IF ( ABS(HLAND(MCUT-1)) .GE. ABS(HLAND(MCUT-2)) ) 1 H(MCUT) = (H(MCUT) + H(MCUT-1)) / 2.0 IF (H(MCUT) .LE. 0.0) H(MCUT)=H(MCUT-1)/2.0 GO TO 260 C NO CONVERGENCE - PRINT DIAGNOSTIC DATA 250 WRITE(IU6, 570) WRITE(IU6, 580) (MCUT, H(MCUT), MCUT, HLAND(MCUT), MCUT = 1,10) GO TO 270 C SET UP FOR NEW START-OF-FLARE ITERATION 260 DE = DST TI = TST GAMFLT = GAMST IA = TST + 1 HT = HST ALPH1 = ALPHST VE = VST HSTOP = H(MCUT) I = 2 GO TO 60 C LANDING DISTANCE IS OBTAINED FROM INTERPOLATION OF APPROACH PATH C DATA USING THE OBSTACLE HEIGHT 270 ICNT = I - 1 DOBST = XINT1(OBSLD,ALT,ICNT,D ) TOBST = XINT1(OBSLD,ALT,ICNT,T ) VOBST = XINT1(OBSLD,ALT,ICNT,V ) AOBST = XINT1(OBSLD,ALT,ICNT,ALP ) THOBST = XINT1(OBSLD,ALT,ICNT,TH ) DST = DST - DOBST DFLAR = DFLAR - DOBST TST = TST - TOBST TFLAR = TFLAR - TOBST C PRINT OUT DATA FROM START OF APPROACH TO TOUCHDOWN IF ( IFLAG .GT. 0 .AND. ITIME .GT. 0 ) THEN WRITE(IU6, 590) WRITE(IU6, 600) (T(J)-TOBST, D(J)-DOBST, ALT(J), V(J), EM(J), 1 GAM(J), ALP(J), TANG(J), TH(J), CLL(J), CDD(J), 2 CLL(J)/CDD(J), ELOD(J), J = 1,ICNT) ENDIF C START ROLLOUT CALCULATIONS FOR LANDING CDSP = 0.0 CLSP = 0.0 FMU = ROLLMU SPOIL = 0.0 BRAKE = 0.0 REVRS = 0.0 REVST = 0.0 TTD = TI DTD = DE - DOBST VTD = VE ALPHTD = ALPH1 280 DELT = DELTRN TIA = TI - TTD + DELT C SET TIA TO NEXT EVENT IF APPROPRIATE IF ( TIA .GT. TISP .AND. SPOIL .EQ. 0.0 ) TIA = TISP IF ( TIA .GT. TIBR .AND. BRAKE .EQ. 0.0 ) TIA = TIBR IF ( TIA .GT. TIRV .AND. REVST .EQ. 0.0 ) TIA = TIRV IF ( TIA .GT. TICUT .AND. CUTBK .EQ. 0.0 ) TIA = TICUT DELT = TIA + TTD - TI C REVERSE ROTATION TO BRING NOSE WHEEL DOWN TO GROUND 290 IF ( (IA - TI) .GT. 1 ) IA = IA - 1 IF ( ALPNU .EQ. ALPRUN ) GO TO 310 ALPNU = ALPH1 - VANGL * DELT / 2.0 ALPH1 = ALPH1 - VANGL * DELT IF ( ALPH1 .GT. ALPRUN ) GO TO 300 ALPNU = (ALPH1 + VANGL * DELT + ALPRUN) / 2.0 ALPH1 = ALPRUN c ohad 16/7/08 - 0.0d0 rather than 0. c 300 CALL GEFECT ( ALPNU, 0.0, 0.0, ALPLD, CLLD, CDLD, CDMLD, CL, CDG, c 1 AR*ARGEF, WHGT, SPAN ) 300 CALL GEFECT ( ALPNU, 0.0d0, 0.0d0, ALPLD, CLLD, CDLD, CDMLD, CL, 1 CDG, AR*ARGEF, WHGT, SPAN ) CDW = CDG 310 VO = VE - ACCH * DELT / 2.0 RHOS = RHOA * VO * VO CDG = CDW + CDGR + CDSP + CDREV*REVRS DRAG = CDG * RHOS CLIFT = (CL + CLSP + CLREV*REVRS) * RHOS FORCV = CLIFT - GROSWT FFRICT = 0.0 IF ( FORCV .LT. 0.0 ) FFRICT = -FMU * FORCV THRU = THM1 IF ( CUTBK .GT. 0.0 ) THRU = XINT1( VO,VELLD,10,THRLD ) IF ( REVRS .GT. 0.0 ) THRU = (1. - REVRS) * THRU + 1 REVRS * RVFACT * XINT1( VO,VELRV,10,THRRV ) FORCH = FFRICT + DRAG - THRU * NE ACCH = FORCH / GROSWT * G C CONSTRAIN DECELERATION IF LIMIT IS EXCEEDED IF ( ACCH .GT. ACCLIM ) ACCH = ACCLIM DE = DE + (VE - ACCH * DELT / 2.0) * DELT TI = TI + DELT VE = VE - ACCH * DELT IF ( IFLAG .EQ. 0 .OR. ITIME .EQ. 0 ) GO TO 330 IF ( TIA .EQ. TISP .OR. TIA .EQ. TIBR .OR. 1 TIA .EQ. TICUT .OR. ISTOP .EQ. 1 ) GO TO 320 IF ( TI .LT. IA ) GO TO 330 C PRINT DATA AT ONE SECOND INTERVALS OR AT EVENT 320 VP = VE / SPD TP = ALPH1 + DELTLP AP = 0.0 THP = THRU * NE EP = VE / SPDSND IF ( VE .GT. 0. .OR. ISTOP .EQ. 1 ) 1 WRITE(IU6, 600) TI-TOBST, DE-DOBST, AP, VP, EP, AP, ALPH1, TP, 2 THP, CL+CLSP+REVRS*CLREV, CDG, (CL+CLSP)/CDG, ACCH IA = IA + 1 C DEPLOY SPOILERS 330 IF ( TIA .NE. TISP ) GO TO 340 CDSP = CDSPOL CLSP = CLSPOL SPOIL = 1.0 DSP = DE - DOBST TSP = TI - TOBST ALPSP = ALPH1 VSP = VE C APPLY BRAKES 340 IF ( TIA .NE. TIBR ) GO TO 350 BRAKE = 1.0 DBRK = DE - DOBST TBRK = TI - TOBST ALPBRK = ALPH1 VBRK = VE FMU = BRAKMU C REVERSE THRUST 350 IF ( TIA .NE. TIRV ) GO TO 360 REVRS = 1.0 REVST = 1.0 DREV = DE - DOBST TREV = TI - TOBST ALPREV = ALPH1 VREV = VE C CUT BACK ENGINES 360 IF ( TIA .EQ. TICUT ) CUTBK = 1.0 IF ( ISTOP .EQ. 1 ) GO TO 370 C REVERSE THRUST CUTOFF IF ( REVRS .GT. 0. ) THEN IF ( REVRS .LT. .999 ) THEN REVRS = 0. ELSE VPR = 2.*VE - VPR IF ( VPR .LT. REVCUT ) REVRS = (VE-REVCUT) / (VE-VPR) ENDIF VPR = VE ENDIF C IF VELOCITY LESS THAN 0.0 ADJUST AND DO 1 MORE IF ( VE .GT. 0.0 ) GO TO 280 TI = TI - DELT VE = VE + ACCH * DELT DE = DE - (VE - ACCH * DELT / 2.0) * DELT DELT = VE / ACCH ISTOP = 1 GO TO 290 C END OF LOOP - AIRCRAFT HAS STOPPED 370 CONTINUE TTD = TTD - TOBST TSTOP = TI - TOBST DSTOP = DE - DOBST VFLAR = VFLAR / SPD VTD = VTD / SPD VSP = VSP / SPD VBRK = VBRK / SPD VREV = VREV / SPD FDLNGT = DSTOP / FARFCT IF ( IFLAG .LE. 0 ) GO TO 400 C PRINT LANDING RESULTS WRITE(IU6, 620) WRITE(IU6, 650) OBSLD, VOBST, ZERO, ZERO, AOBST, OBSLD, 1 VFLAR, TFLAR, DFLAR, ALPFLR, HFLAR, 2 VTD, TTD, DTD, ALPHTD, ZERO WRITE(IU6, 660) VSP, TSP, DSP, ALPSP, ZERO WRITE(IU6, 670) VBRK, TBRK, DBRK, ALPBRK, ZERO IF ( REVRS * RVFACT .NE. 0.0 ) WRITE(IU6,680 ) 1 VREV, TREV, DREV, ALPREV, ZERO WRITE(IU6, 690) ZERO, TSTOP, DSTOP, ALPRUN, ZERO FVS = 1.3 - .1*IFITE WRITE(IU6, 630) VSTALL, FVS, FVS*VSTALL, VMU/SPD/1.05, VMU/SPD WRITE(IU6, 640) V2/SPD, ALP2, GAM2*100., FORCE2 IF ( FORCE2 .LT. FTOL ) WRITE(IU6, 710) IF ( IFITE .EQ. 0 ) THEN WRITE(IU6, 700) FARFCT, FDLNGT ELSE WRITE(IU6, 720) FDLNGT ENDIF 400 RETURN 430 FORMAT (/32X,35HDRAG POLAR - GEAR DRAG NOT INCLUDED/) 440 FORMAT (5X,15HANGLE OF ATTACK,4X,10F10.2) 450 FORMAT (5X,16HLIFT COEFFICIENT,3X,10F10.4) 460 FORMAT (5X,16HDRAG COEFFICIENT,3X,10F10.4) 470 FORMAT (/5X,7HCDMLD =,1F7.4,9X,8HCDGEAR =,F7.4,9X,8HCDEOUT =, 1 F7.4,9X,7HCLLDM =,F7.4,8X,16HLANDING WEIGHT =,F10.1) 475 FORMAT (/5X,7HCLMAX =,F7.4,13H FOR ALMXLD =,F7.2) 480 FORMAT (/32X,33HIDLE NET THRUST VALUES FOR ENGINE/) 490 FORMAT (/32X,32HREVERSE THRUST VALUES FOR ENGINE/) 500 FORMAT (5X,9HVELOCITY ,10F11.1) 510 FORMAT (5X,9HTHRUST ,10F11.1) 530 FORMAT (/10X,60HITERATION OF CONSTANT VELOCITY ANGLE OF ATTACK IS 1INCOMPLETE ) 540 FORMAT (10X,6HALPHE(,I2,4H) = ,F9.4,5X,7HDELFOR(,I2,4H) = , 1 F11.2) 550 FORMAT (/10X,65HUNABLE TO ITERATE ON FLARE NORMAL ACCELERATION - P 1ROGRAM CONTINUE ) 560 FORMAT (10X,6HALPHE(,I2,4H) = ,F9.4,5X,4HACN(,I2,4H) = ,F9.4) 570 FORMAT (/10X,64HITERATION OF TOUCHDOWN ALTITUDE IS INCOMPLETE - PR 1OGRAM CONTINUE) 580 FORMAT (10X,2HH(,I2,4H) = ,F10.4,5X,6HHLAND(,I2,4H) = ,F10.4) 590 FORMAT (//2X,4HTIME,5X,8HDISTANCE,3X,8HALTITUDE,3X,8HVELOCITY,5X, 1 4HMACH,6X,5HGLIDE,4X,6HATTACK,5X,6HENGINE,5X,6HENGINE,5X,4HLIFT, 2 5X,4HDRAG,6X,3HL/D,4X,6HDECEL.,/45X,6HNUMBER,5X,5HSLOPE,5X, 3 5HANGLE,4X,9HINCIDENCE,3X,6HTHRUST,4X,6HCOEFF.,3X,6HCOEFF.,4X, 4 5HRATIO,/8H SECONDS,5X,4HFEET,7X,4HFEET,7X,5HKNOTS,15X,7HDEGREES, 5 3X,7HDEGREES,4X,7HDEGREES,4X,6HPOUNDS,31X,6HFT/S/S,/) 600 FORMAT (F7.2,3F11.2,F11.4,2F10.3,F11.3,F12.1,2F9.4,2F9.2) 610 FORMAT (/'# LANDING PERFORMANCE RESULTS') 620 FORMAT (/' LANDING PERFORMANCE',T33,'VELOCITY TIME',T53, 1 'DISTANCE ALPHA ALTITUDE',/,T35, 2 'KNOTS SEC. FEET DEG. FEET',/) 630 FORMAT (' STALL SPEED (VS)',T31,F10.2,/F9.2,' VS',T31,F10.2,/ 1 /' UNSTICK SPEED (VU)',T31,F10.2,/' 1.05 VU',T31,F10.2,/) 640 FORMAT (' MISSED APPROACH CLIMB',T31,F10.2,T61,F9.2,// 1 ' FLIGHT PATH SLOPE = ',F8.2,' PERCENT' / 2 ' NET THRUST = ',F8.0,' POUNDS' ) 650 FORMAT (F8.0,' FOOT OBSTACLE',T31,F10.2,F9.2,F11.2,2F9.2,/ 1 ' START OF FLARE',T31,F10.2,F9.2,F11.2,2F9.2,/ 2 ' TOUCHDOWN ', T31,F10.2,F9.2,F11.2,2F9.2) 660 FORMAT(5X,'SPOILER ACTUATION',T31,F10.2,F9.2,F11.2,2F9.2) 670 FORMAT(5X,'WHEEL BRAKES APPLIED',T31,F10.2,F9.2,F11.2,2F9.2) 680 FORMAT(5X,'THRUST REVERSAL',T31,F10.2,F9.2,F11.2,2F9.2) 690 FORMAT(5X,'END OF LANDING',T31,F10.2,F9.2,F11.2,2F9.2,/) 700 FORMAT(/' FAR LANDING FIELD LENGTH = LANDING DISTANCE /',F3.1, 1 T50,F11.2,' FEET' ) 710 FORMAT (/51H * * * FAILED MISSED APPROACH CLIMB CRITERION * * * ) 720 FORMAT(/' LANDING DISTANCE ',T50,F11.2,' FEET' ) END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE DEFPRO IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) C INPUT DATA FOR TAKEOFF NOISE PROFILE COMMON /UNITS / IU5, IU6, IU7, IU8, IU9, IU16, IU17, IU18 COMMON /SEGDAT/ DSTP(20), TSTP(20), HSTP(20), VSTP(20), DLT(20), 1 AFX(20), GFX(20), VFX(20), ENGSC(20), HMN(20), 2 GRAEO(20), GROEO(20), SPRT(20), IFX(20), IFLP(20), 3 NSEG, NTIME, IPCMAX COMMON /KEYDAT/ KEYS(20) COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /PRAERO/ ALPRO(10,10), CLPRO(10,10), CDPRO(10,10), 1 DFLAP(10), TXF, ALPMIN, GAMLIM COMMON /NOISEP/ NOPRO, NPFILE, NOISE CHARACTER*4 KEYS, KEY NAMELIST/PROIN/ ALPRO, CLPRO, CDPRO, NPOL, DFLAP, NTIME, NPFILE, 1 TXF, SPRATE, ALPMIN, IPCMAX, GAMLIM NAMELIST/SEGIN/ KEY, NFLAP, IFIX, DSTOP, TSTOP, HSTOP, VSTOP, 1 AFIX, GFIX, VFIX, ENGSCL, HMIN, DELT, GRDAEO, 2 GRDOEO, SPRATE C INITIALIZE AND READ AERODYNAMIC DATA DO 10 I = 1,10 ALPRO(I,1) = ALPTO(I) CLPRO(I,1) = CLTO(I) 10 CDPRO(I,1) = CDTO(I) NPOL = 1 NTIME = 0 IPCMAX = 1 SPRATE = 0.1 READ ( IU5, NML=PROIN, ERR=9000, END=9000 ) C DEFAULT VALUES - FIRST, PARAMETERS THAT DEFAULT TO PREVIOUS VALUES NSEG = 1 NFLAP = 1 IFIX = 1 ENGSCL = 1. GRDAEO = 2.29061 GRDOEO = 0.0 C THEN, PARAMETERS THAT MUST BE INPUT TO BE USED 20 KEY = 'CHAN' DSTOP = 0. TSTOP = 0. HSTOP = 0. VSTOP = 0. HMIN = 0. AFIX = 0. GFIX = 0. VFIX = 0. DELT = 1. C READ TAKEOFF AND CLIMB SEGMENT DATA AND FILL ARRAYS READ ( IU5, NML=SEGIN, ERR=9002, END=9002 ) KEYS(NSEG) = KEY IFX(NSEG) = IFIX IFLP(NSEG) = NFLAP DSTP(NSEG) = DSTOP TSTP(NSEG) = TSTOP SPRT(NSEG) = SPRATE IF ( KEY .EQ. 'OBST' .AND. HSTOP .LE. 0. ) HSTOP = OBSTO HSTP(NSEG) = HSTOP VSTP(NSEG) = VSTOP HMN(NSEG) = HMIN IF ( HSTOP .GT. 0. .AND. HSTOP .LT. HMIN ) HSTP(NSEG) = HMIN AFX(NSEG) = AFIX GFX(NSEG) = GFIX VFX(NSEG) = VFIX ENGSC(NSEG) = ENGSCL GRAEO(NSEG) = GRDAEO GROEO(NSEG) = GRDOEO IF ( KEY .EQ. 'LIFT' ) DELT = DELTRO IF ( KEY .EQ. 'OBST' ) DELT = DELTCL DLT(NSEG) = DELT C CHECK FOR FINAL SEGMENT, IF NOT, READ NEXT SEGMENT IF ( KEY .EQ. 'LAST' ) GO TO 30 NSEG = NSEG + 1 ENGSCL = 0. GO TO 20 C LIMIT INTERMEDIATE SEGMENTS 30 DO 40 I = 2,NSEG J = NSEG - I + 1 IF ( DSTP(J) .LE. 0. ) DSTP(J) = DSTP(J+1) IF ( TSTP(J) .LE. 0. ) TSTP(J) = TSTP(J+1) IF ( HSTP(J) .LE. 0. ) HSTP(J) = HSTP(J+1) 40 CONTINUE C OUTPUT AERODYNAMIC DATA WRITE(IU6, 120) NTIME, NPFILE, IPCMAX, TXF, ALPMIN, GAMLIM 120 FORMAT(///'# NAMELIST $PROIN',/ 1 ' INPUT DATA FOR CLIMB PROFILE FOR NOISE CALCULATIONS',// 2 ' DESCRIPTION',16X,'NAME',9X,'VALUE DIMENSIONS',// 3 ' PROFILE PRINT SWITCH NTIME ',I11,/ 4 ' PROFILE OUTPUT FILE SWITCH NPFILE ',I11,/ 5 ' MAXIMUM POWER CODE IPCMAX ',I11,/ 6 ' TAXI OUT FUEL TXF ',F11.2,' LB',/ 7 ' MINIMUM CLIMB ALPHA ALPMIN ',F11.2,' DEG',/ 8 ' MINIMUM FLIGHT PATH ANGLE GAMLIM ',F11.2,' DEG') WRITE(IU6, 50) 50 FORMAT (/' TAKEOFF AND CLIMB DRAG POLARS - GEAR DRAG NOT', 1 ' INCLUDED') DO 60 I = 1,NPOL 60 WRITE(IU6, 70) DFLAP(I), (ALPRO(J,I), J = 1,10), 1 (CLPRO(J,I), J = 1,10), (CDPRO(J,I), J = 1,10) 70 FORMAT(/' FLAP SETTING DFLAP =',F6.2, 1 /' ANGLE OF ATTACK ALPRO ',10F10.2, 2 /' LIFT COEFFICIENT CLPRO ',10F10.6, 3 /' DRAG COEFFICIENT CDPRO ',10F10.6 ) C OUTPUT SEGMENT DEFINITION DATA WRITE(IU6, 100) (I, KEYS(I), IFX(I), IFLP(I), DSTP(I), TSTP(I), 1 VSTP(I), HSTP(I), HMN(I), AFX(I), GFX(I), VFX(I), 2 ENGSC(I), DLT(I), GRAEO(I), GROEO(I), SPRT(I), 3 I = 1,NSEG) 100 FORMAT(//'# NAMELISTS $SEGIN',/ 1 ' TAKEOFF AND CLIMB SEGMENT DEFINITION INPUT DATA',// 1 ' SEGMENT KEY IFIX NFLAP DSTOP TSTOP VSTOP ', 2 'HSTOP HMIN AFIX GFIX VFIX ENGSCL DELT ', 3 'GRDAEO GRDOEO SPRATE', 4 //(I5,5X,A4,I5,I6,3X,3F8.1,2F9.1,2F8.2,F8.1,F9.3,F7.2,3F7.3)) RETURN 9000 WRITE(IU6,9001) IU5 9001 FORMAT (//' ERROR READING NAMELIST $PROIN FROM UNIT',I3,/, 2 ' PROGRAM ABORTED IN SUBROUTINE DEFPRO.',/) STOP 9002 WRITE(IU6,9003) IU5 9003 FORMAT (//' ERROR READING NAMELIST $SEGIN FROM UNIT',I3,/, 2 ' PROGRAM ABORTED IN SUBROUTINE DEFPRO.',/) STOP END CCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE SEPARATOR CCCCCCCCCCCCCCCCCCCCCCCCC SUBROUTINE PROFIL (GROSWT, ARN, SW, GLOV, NENG, IPRINT ) C COMPUTE TAKEOFF AND CLIMB PROFILE FOR NOISE CALCULATION C GROSWT = AIRCRAFT CURRENT RAMP WEIGHT C ARN,SW,GLOV = CURRENT ASPECT RATIO, WING AREA, AND GLOVE AREA C NENG = NUMBER OF ENGINES C IPRINT = PRINT CONTROL PARAMETER IMPLICIT DOUBLE PRECISION (A-H,O-Z) c ohad 15/7/08 c IMPLICIT INTEGER*8 (I-N) IMPLICIT INTEGER*4 (I-N) COMMON /UNITS / IU5, IU6, IU7, IU8, IU9, IU16, IU17, IU18 COMMON /XFLOPC/ IXFL, IU19, IU20 COMMON /BALFLD/ ALPRUN, ARGEF, BRAKMU, CDGRO, CDSPOL, CLSPOL, 1 RHOA, ROLLMU, TIBRA, TICUT, TINC, TISPA, VANGL, 2 WHGT, PILOTT, CDEOT, ITIME, ISPOL, IREV COMMON /SCRTCH/ T(500), D(500), ALT(500), V(500), GAM(500), 1 ALP(500), TH(500), CLL(500), CDD(500), ACL(500), 2 WT(500), TTM(500), FLAPA(500), RDUM(1500), 3 IGR(500), KA(20), KSEG, KDUM(2679) COMMON /TOCOMM/ CDMT ,DMT ,ALPROT,DELTCL,SWREF ,ARRET ,VROTAT, 1 OBSTO ,DELTRO,DELVTO,ALMXTO,TIGEAR,CLTOM ,CDMTO , 2 CDDP(10), CLDPOC(10), ALPTO(10), CLTO(10), 3 CDTO(10), IBAL COMMON /TOLTH / APA, ANS1, DTCT, SPDSND, THFACT, THREF, THRTO(10), 1 THRLD(10), VELTO(10), VELLD(10), INTHTO, INTHLD COMMON /ROTSPD/ VROT, VEE2 COMMON /PRAERO/ ALPRO(10,10), CLPRO(10,10), CDPRO(10,10), 1 DFLAP(10), TXF, ALPMIN, GAMLIM COMMON /SEGDAT/ DSTP(20), TSTP(20), HSTP(20), VSTP(20), DLT(20), 1 AFX(20), GFX(20), VFX(20), ENGSC(20), HMN(20), 2 GRAEO(20), GROEO(20), SPRT(20), IFX(20), IFLP(20), 3 NSEG, NTIME, IPCMAX COMMON /KEYDAT/ KEYS(20) COMMON /NOISEP/ NOPRO, NPFILE, NOISE COMMON /TAXFUL/ TAXOFL, ITXOUT CHARACTER*4 KEYS, KEY DIMENSION VIT(10), ALWR(10), HFOR(10), DELFOR(10) DATA RAD /0.0174533/ C SCALE AERODYNAMIC DRAG ASSUMING PARABOLIC POLAR C INITIALIZE CONSTANTS AND CONFIGURATION DATA SPAN = SQRT( ARN * (SW - GLOV) ) CDM = CDMT + DMT / SW DO 10 J = 1,5 DO 10 I = 1,10 CDPRO(I,J) = (CDPRO(I,J) - CDMTO) * ARRET / ARN + CDM 10 CONTINUE CDGEAR = CDGRO / SW CDEOUT = CDEOT / SW CDMTO = CDM ARRET = ARN G = 9.80665/.3048 ZERO = 0. KSEG = NSEG SPD = 1852./(.3048*3600.) NE = NENG RHOA = ANS1 * SW * 0.5 IX = 0 ISEG = 1 CWT = GROSWT - TXF IF ( TXF .LT. 0. ) CWT = GROSWT - TAXOFL ALFROT = ALPROT IF ( ALFROT .GT. ALMXTO ) ALFROT = ALMXTO C CALCULATE PROFILE FROM START OF GROUND ROLL C UNTIL ROTATION SPEED IS REACHED C SET UP INITIAL CONDITIONS AT BRAKE RELEASE IF ( IPRINT .GT. 0 ) WRITE(IU6, 560) 560 FORMAT(///'# PROFILE FOR NOISE CALCULATIONS',/ 1 /' TAKEOFF AND CLIMB PROFILE SEGMENT RESULT SUMMARY',// 2 ' KEY TIME HEIGHT DISTANCE SPEED GAMMA', 3 ' ALPHA WEIGHT FLAPS CL L/D EGEAR THRUST', 4 ' VJET T/TMAX',/ ) IA = 1 VE = 0.0 TTO = ENGSC(1) D(IA) = 0.0 T(IA) = 0.0 V(IA) = 0.0 ALT(IA) = 0.0 GAM(IA) = 0.0 ALP(IA) = ALPRUN WT(IA) = CWT IFP = IFLP(1) FLAPA(IA) = DFLAP(IFP) IGR(IA) = 1 C AERODYNAMICS FOR FIRST SEGMENT c ohad 16/7/08 - 0.0d0 rather than 0. c CALL GEFECT ( ALPRUN, 0., 0., ALPRO(1,IFP), CLPRO(1,IFP), c 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) CALL GEFECT ( ALPRUN, 0.0d0, 0.0d0, ALPRO(1,IFP), CLPRO(1,IFP), 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) CDG = CDG + CDGEAR CDP = XINT1( VE,VELTO,10,CDDP ) DCL = XINT1( VE,VELTO,10,CLDPOC ) / CL CLL(IA) = CL + DCL CDD(IA) = CDG + CDP STINC = NE * SIN( TINC * RAD ) CTINC = NE * COS( TINC * RAD ) C INITIAL THRUST AND ACCELERATION THRU = TTO CALL ENINT (ZERO, APA, THRU, FFO, 2, TMAX, ITD, IPCMAX) TH(IA) = NE * THRU IF ( IPCMAX .GT. 1 ) 1 CALL ENINT (VE/SPDSND, APA, XTT, XFF, 1, TMAX, ITD, 1 ) TTM(IA) = THRU / TMAX ACO = (THRU * CTINC - ROLLMU * CWT) * G / CWT ACL(IA) = ACO C BEGIN LOOP ON GROUND RUN SEGMENTS 20 IFP = IFLP(ISEG) VSTOP = VSTP(ISEG) * SPD DSTOP = DSTP(ISEG) TSTOP = TSTP(ISEG) IF ( ENGSC(ISEG) .GT. 0. ) ENGSCL = ENGSC(ISEG) KEY = KEYS(ISEG) IF ( VSTOP .LE. 0. .AND. KEY .EQ. 'ROTA' ) VSTOP = VROT DELTAV = DELVTO IF ( ISEG .EQ. 1 ) GO TO 30 c ohad 16/7/08 - 0.0d0 rather than 0. c CALL GEFECT ( ALPRUN, 0., 0., ALPRO(1,IFP), CLPRO(1,IFP), c 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) CALL GEFECT ( ALPRUN, 0.0d0, 0.0d0, ALPRO(1,IFP), CLPRO(1,IFP), 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) CDG = CDG + CDGEAR C INCREMENT VELOCITY UNTIL ROTATION SPEED OR STOP IS REACHED 30 V1 = V(IA) + DELTAV IF ( V1 .LT. VSTOP ) GO TO 40 V1 = VSTOP DELTAV = V1 - V(IA) IX = 1 40 CDP = XINT1( V1,VELTO,10,CDDP ) DRAG = (CDG + CDP) * V1 * V1 * RHOA DELT = DELTAV / ACO THRU = ENGSCL DESP = DELT*SPRT(ISEG) IF ( ABS(THRU-TTO) .GT. DESP .AND. DESP .GT. 0. ) THEN IF ( THRU .GT. TTO ) THRU = TTO + DESP IF ( THRU .LT. TTO ) THRU = TTO - DESP ENDIF TTOO = THRU CALL ENINT (V1/SPDSND, APA, THRU, FF, 2, TMAX, ITD, IPCMAX) DCL = XINT1( V1,VELTO,10,CLDPOC ) / CL CLIFT = (CL + DCL) * RHOA * V1 * V1 + STINC * THRU CWT = WT(IA) - DELT * (FF + FFO) * NE / 7200. ACC = (THRU*CTINC - DRAG - ROLLMU * (CWT - CLIFT)) * G / CWT C TIME AND DISTANCE ARE CALCULATED FOR THE VELOCITY STEP DELT = 2. * DELTAV / (ACC + ACO) IA = IA + 1 IF ( IA .GT. 100 .OR. ACC .LT. 0. ) GO TO 500 T(IA) = T(IA-1) + DELT D(IA) = D(IA-1) + DELT * (V(IA-1) + (2.*ACO + ACC) * DELT / 6.) V(IA) = V1 ALT(IA) = 0.0 GAM(IA) = 0.0 ALP(IA) = ALPRUN FLAPA(IA) = DFLAP(IFP) IGR(IA) = 1 CLL(IA) = CL + DCL CDD(IA) = CDG + CDP TH(IA) = NE * THRU IF ( IPCMAX .GT. 1 ) 1 CALL ENINT (V1/SPDSND, APA, XTT, XFF, 1, TMAX, ITD, 1 ) TTM(IA) = THRU / TMAX WT(IA) = WT(IA-1) - DELT * (FF + FFO) * NE / 7200. FFO = FF ACL(IA) = ACC ISTOP = 0 C CHECK FOR END OF SEGMENT DL = 0. IF ( DSTOP .LE. 0. .OR. D(IA) .LT. DSTOP ) GO TO 50 ISTOP = 1 DL = (D(IA) - DSTOP) / (D(IA) - D(IA-1)) 50 IF ( TSTOP .LE. 0. .OR. T(IA) .LT. TSTOP ) GO TO 60 ISTOP = 1 DLP = (T(IA) - TSTOP) / (T(IA) - T(IA-1)) DL = MAX(DL,DLP) 60 IF ( ISTOP .EQ. 0 ) GO TO 70 D(IA) = (1. - DL) * D(IA) + DL * D(IA-1) T(IA) = (1. - DL) * T(IA) + DL * T(IA-1) V(IA) = (1. - DL) * V(IA) + DL * V(IA-1) WT(IA) = (1. - DL) * WT(IA) + DL * WT(IA-1) CLL(IA) = (1. - DL) * CLL(IA) + DL * CLL(IA-1) CDD(IA) = (1. - DL) * CDD(IA) + DL * CDD(IA-1) TH(IA) = (1. - DL) * TH(IA) + DL * TH(IA-1) TTM(IA) = (1. - DL) * TTM(IA) + DL * TTM(IA-1) ACL(IA) = (1. - DL) * ACL(IA) + DL * ACL(IA-1) TTO = (1. - DL) * TTOO + DL * TTO GO TO 80 70 TTO = TTOO IF ( IX .GT. 0 .OR. CLIFT .GT. CWT ) GO TO 80 ACO = ACC GO TO 30 C CHECK FOR START OF ROTATION 80 KA(ISEG) = IA IF ( IPRINT .GT. 0 ) WRITE(IU6, 630) KEY, T(IA), ALT(IA), D(IA), 1 V(IA)/SPD, GAM(IA), ALP(IA), WT(IA), FLAPA(IA), CLL(IA), 2 CLL(IA)/CDD(IA), FLOAT(IGR(IA)), TH(IA), ZERO, TTM(IA) ISEG = ISEG + 1 IF ( KEY .NE. 'ROTA' ) GO TO 20 C INITIALIZE FOR START OF ROTATION VE = V(IA) DE = D(IA) TI = T(IA) DELT = T(IA) - T(IA-1) DACC = 0. IF ( DELT .GT. .0001 ) DACC = (ACL(IA) - ACL(IA-1)) / DELT ACO = ACL(IA) ALPOL = ALPRUN DELT = DELTRO ALPH1 = ALPRUN DELF = 1.0 IL = 0 IFP = IFLP(ISEG) IF ( ENGSC(ISEG) .GT. 0. ) ENGSCL = ENGSC(ISEG) C ROTATION LOOP - ROTATE AT SPECIFIED RATE (VANGLE) AND C ESTIMATE VELOCITY AT THE END OF THE TIME STEP 90 DELTAL = VANGL * DELT ALPH1 = ALPH1 + DELTAL M = 0 DELTAV = DELT * (2.*ACO + DACC*DELT) / 2. IF ( ALPH1 .GT. ALFROT ) ALPH1 = ALFROT c ohad 16/7/08 - 0.0d0 rather than 0. c CALL GEFECT ( ALPH1, 0., 0., ALPRO(1,IFP), CLPRO(1,IFP), c 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) CALL GEFECT ( ALPH1, 0.0d0, 0.0d0, ALPRO(1,IFP), CLPRO(1,IFP), 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) C LOOP TO CONVERGE VELOCITY AT THE END OF THE TIME STEP C COMPUTE VERTICAL LIFT AND HORIZONTAL ACCELERATION 100 V1 = VE + DELTAV CDP = XINT1( V1,VELTO,10,CDDP ) DRAG = (CDG + CDGEAR + CDP) * RHOA * V1 ** 2 THRU = ENGSCL DESP = DELT*SPRT(ISEG) IF ( ABS(THRU-TTO) .GT. DESP .AND. DESP .GT. 0. ) THEN IF ( THRU .GT. TTO ) THRU = TTO + DESP IF ( THRU .LT. TTO ) THRU = TTO - DESP ENDIF TTOO = THRU CALL ENINT (V1/SPDSND, APA, THRU, FF, 2, TMAX, ITD, IPCMAX) CLP = XINT1( V1,VELTO,10,CLDPOC ) DCL = CLP / CL DELTLP = ALPH1 - ALPRUN CLIFT = (CL + DCL) * RHOA * V1 ** 2 + NE * SIN( (TINC + 1 DELTLP) * RAD ) * THRU CWT = WT(IA) - DELT * (FF + FFO) * NE / 7200. FRICT = ROLLMU * (CWT - CLIFT) IF ( FRICT .LT. 0.0 ) FRICT = 0.0 TNET = THRU * NE * COS( (TINC + DELTLP) * RAD ) FORC = TNET - DRAG - FRICT ACC = FORC * G / CWT DVO = DELTAV IF ( DELT .GT. 0. ) DACC = (ACC - ACO) / DELT DELTAV = DELT * (ACO + ACC) / 2. IF ( IL .GT. 0 ) GO TO 110 M = M + 1 IF ( ABS(DELTAV-DVO) .GT. .001 .AND. M .LT. 10 ) GO TO 100 IF ( CLIFT .GT. CWT ) GO TO 110 TI = TI + DELT DE = DE + DELT * (VE + (2. * ACO + ACC) * DELT / 6.) VE = VE + DELTAV DELF = CLIFT - CWT ACO = ACC ALPOL = ALPH1 IA = IA + 1 IF ( IA .GT. 200 ) GO TO 500 T(IA) = TI D(IA) = DE V(IA) = VE ALT(IA) = 0.0 GAM(IA) = 0.0 WT(IA) = CWT FLAPA(IA) = DFLAP(IFP) IGR(IA) = 1 ALP(IA) = ALPH1 TH(IA) = THRU * NE IF ( IPCMAX .GT. 1 ) 1 CALL ENINT (VE/SPDSND, APA, XTT, XFF, 1, TMAX, ITD, 1 ) TTM(IA) = THRU / TMAX WT(IA) = WT(IA-1) - DELT * (FF + FFO) * NE / 7200. FFO = FF TTO = TTOO CLL(IA) = CL + DCL CDD(IA) = CDG + CDGEAR + CDP ACL(IA) = ACC GO TO 90 C ITERATE UNTIL TIME OF LIFTOFF IS DETERMINED 110 IL = IL + 1 VIT(IL) = DELT DELFOR(IL) = CLIFT - CWT ALWR(IL) = ALPH1 HFOR(IL) = FORC C IF THE NET FORCE = 0, LIFTOFF HAS OCCURRED IF ( ABS( DELFOR(IL) ) .LT. 0.00001 * GROSWT ) GO TO 150 IF ( IL .GT. 1 ) GO TO 120 C FIRST ITERATION DELT = DELT * (1. - DELFOR(IL) / (DELFOR(IL) - DELF)) IF ( DELT .LT. 0.0 ) DELT = 0.0 GO TO 130 C SUBSEQUENT ITERATIONS - LINEAR INTERPOLATION 120 IF ( IL .GE. 10 ) GO TO 140 DELT = VIT(IL) - (VIT(IL) - VIT(IL-1)) * DELFOR(IL) / 1 (DELFOR(IL) - DELFOR(IL-1)) IF ( DELT .LE. 0.0 ) DELT = VIT(IL) / 2.0 IF ( DELT .LE. 0.0 ) GO TO 150 CHECK = DELFOR(IL)*DELFOR(IL-1) C TRY INTERVAL HALVING IF( IL.GT.5 .AND. CHECK.LT.0. ) DELT = (VIT(IL)+VIT(IL-1))/2.0 130 ALPH1 = ALPOL GO TO 90 140 IF ( ABS( VIT(IL) - VIT(IL-1) ) .LT. 0.001 ) GO TO 150 C NO CONVERGENCE - PRINT DIAGNOSTIC DATA WRITE(IU6, 550) (IL, VIT(IL), DELFOR(IL), ALWR(IL), HFOR(IL), 1 IL = 1,10) 150 DELTAV = (ACC + ACO) * DELT / 2.0 TLO = TI + DELT DLO = DE + DELT * (VE + (2. * ACO + ACC) * DELT / 6.) VLO = VE + DELTAV ACO = ACC IA = IA + 1 IF ( IA .GT. 300 ) GO TO 500 T(IA) = TLO D(IA) = DLO V(IA) = VLO ALT(IA) = 0.0 GAM(IA) = 0.0 WT(IA) = CWT FLAPA(IA) = DFLAP(IFP) IGR(IA) = 1 ALP(IA) = ALPH1 TH(IA) = THRU * NE IF ( IPCMAX .GT. 1 ) 1 CALL ENINT (VLO/SPDSND, APA, XTT, XFF, 1, TMAX, ITD, 1 ) TTM(IA) = THRU / TMAX WT(IA) = WT(IA-1) - DELT * (FF + FFO) * NE / 7200. FFO = FF TTO = TTOO CLL(IA) = CL + DCL CDD(IA) = CDG + CDGEAR + CDP ACL(IA) = ACC KA(ISEG) = IA KEY = KEYS(ISEG) IF ( IPRINT .GT. 0 ) WRITE(IU6, 630) KEY, T(IA), ALT(IA), D(IA), 1 V(IA)/SPD, GAM(IA), ALP(IA), WT(IA), FLAPA(IA), CLL(IA), 2 CLL(IA)/CDD(IA), FLOAT(IGR(IA)), TH(IA), ZERO, TTM(IA) C COMPUTE TRAJECTORY FROM LIFTOFF UNTIL OBSTACLE HEIGHT IS REACHED VVERT = 0.0 VHORZ = VLO TI = TLO DE = DLO GAMO = 0.0 DELO = 0.0 HOO = 0.0 ACHO = ACO ACVO = 0.0 DACV = 0.0 DGAM = 0.0 MAL = 0 IL = 0 HT = 0.0 DELT = DELTCL GAMFLT = 0.0 ISEG = ISEG + 1 KEY = KEYS(ISEG) IF ( KEY .NE. 'OBST' ) THEN ISEG = ISEG - 1 GO TO 250 ENDIF IFP = IFLP(ISEG) IF ( ENGSC(ISEG) .GT. 0. ) ENGSCL = ENGSC(ISEG) HSTOP = HSTP(ISEG) IF ( HSTOP .LE. 0. ) HSTOP = OBSTO C INCREMENT TIME UNTIL ALTITUDE EXCEEDS OBSTACLE HEIGHT 160 DELTAV = DELT * (2.*ACO + DACC*DELT) / 2. IF ( DELTAV .LT. 0. ) DELTAV = 0. DELTAL = VANGL * DELT ALPOL = ALPH1 M = 0 C CONTINUE ROTATION LIMITED BY ALMXTO ALPH1 = ALPH1 + DELTAL 170 IF ( ALPH1 .GT. ALMXTO ) ALPH1 = ALMXTO GAMFLT = GAMO + DELT * DGAM DELTLP = ALPH1 - ALPRUN HO = HT + DELT * (VVERT + DELT * (3.*ACVO + DELT*DACV) / 6. ) CALL ATMO ( APA+HO, DTCT, DELTA, THETA, ASTAR, TM, RE, HFT ) SPDSND = ASTAR * SPD RHOA = 0.0023769 * SW * DELTA / THETA / 2. CALL GEFECT (ALPH1, HO, GAMFLT, ALPRO(1,IFP), CLPRO(1,IFP), 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) V1 = VE + DELTAV C INCLUDE GEAR DRAG IF IT IS STILL DOWN CDGR = 0.0 IF ( (TI + DELT - TLO) .LE. TIGEAR .AND. TIGEAR .GT. 0. ) 1 CDGR = CDGEAR * COS( ((TI + DELT - TLO) / TIGEAR) * 90.0 * RAD ) IGER = 0 IF ( CDGR .GT. 0. ) IGER = 1 CDP = XINT1( V1,VELTO,10,CDDP ) DRAG = (CDG + CDGR + CDP) * V1 ** 2 * RHOA CLP = XINT1(V1,VELTO,10,CLDPOC) DCL = CLP / CL CLIFT = (CL + DCL) * V1 ** 2 * RHOA THRU = ENGSCL DESP = DELT*SPRT(ISEG) IF ( ABS(THRU-TTO) .GT. DESP .AND. DESP .GT. 0. ) THEN IF ( THRU .GT. TTO ) THRU = TTO + DESP IF ( THRU .LT. TTO ) THRU = TTO - DESP ENDIF TTOO = THRU CALL ENINT (V1/SPDSND, APA+HO, THRU, FF, 2, TMAX, ITD, IPCMAX) CG = COS( GAMFLT * RAD ) SG = SIN( GAMFLT * RAD ) TNETH = THRU * NE * COS( (TINC + DELTLP + GAMFLT) * RAD ) TNETV = THRU * NE * SIN( (TINC + DELTLP + GAMFLT) * RAD ) FORCH = TNETH - CLIFT * SG - DRAG * CG FORCV = TNETV + CLIFT * CG - CWT - DRAG * SG CWT = WT(IA) - DELT * (FF + FFO) * NE / 7200. ACCH = FORCH * G / CWT ACCV = FORCV * G / CWT DACV = (ACCV - ACVO) / DELT HO = HT + DELT * (VVERT + DELT * (2.0 * ACVO + ACCV) / 6.0 ) TVERT = VVERT + DELT * (ACVO + ACCV) / 2.0 THORZ = VHORZ + DELT * (ACHO + ACCH) / 2.0 TV = SQRT(TVERT**2 + THORZ**2) GAMFLT = ATAN(TVERT / THORZ) / RAD DGAM = (GAMFLT - GAMO) / DELT ACC = (ACCH * THORZ + ACCV * TVERT ) / TV DELTAV = TV - VE M = M + 1 IF ( M .EQ. 1 ) GO TO 170 IF ( MAL .GT. 0 ) GO TO 190 IF ( ACC .GE. 0. ) GO TO 210 C IF FLIGHT PATH ACCELERATION IS NEGATIVE, REDUCE ALPHA C AND ITERATE UNTIL ACCELERATION IS ZERO DAL = -0.1 180 MAL = MAL + 1 ALPO = ALPH1 ACACO = ACC ALPH1 = ALPH1 + DAL DELTAV = DELT * ACO / 2. M = 0 GO TO 170 190 IF ( ABS(ACC) .GT. 0.001 .AND. MAL .LT. 10 .AND. ACC .NE. ACACO ) 1 GO TO 200 MAL = 0 GO TO 210 200 DAL = -ACC * (ALPH1 - ALPO) / (ACC - ACACO) GO TO 180 210 IF ( ABS(HO - HSTOP) .LT. 0.01 ) GO TO 230 IF ( IL .GT. 0 ) GO TO 220 IF ( HO .LT. HSTOP ) GO TO 240 C IF HEIGHT EXCEEDS OBSTACLE, ITERATE UNTIL EQUAL 220 DV = (DELT - DELO) * (HO - HSTOP) / (HO - HOO) DELO = DELT HOO = HO DELT = DELT - DV IF ( DELT .LT. 0.0 ) DELT = DELO / 2.0 IF ( DELT .GT. DELTCL ) DELT = (DELTCL + DELO) / 2.0 ALPH1 = ALPOL IL = IL + 1 IF ( IL .LT. 10 ) GO TO 160 230 IL = 10 240 CONTINUE HT = HO HOO = HT DE = DE + DELT * (VHORZ + (2.0 * ACHO + ACCH) * DELT / 6.0) VVERT = TVERT VHORZ = THORZ VE = TV GAMO = GAMFLT IF ( DELT .GT. 0. ) DACC = (ACC - ACO) / DELT ACO = ACC ACHO = ACCH ACVO = ACCV TI = TI + DELT IA = IA + 1 IF ( IA .GT. 400 ) GO TO 500 T(IA) = TI D(IA) = DE V(IA) = VE ALP(IA) = ALPH1 WT(IA) = CWT FLAPA(IA) = DFLAP(IFP) IGR(IA) = IGER TH(IA) = THRU * NE IF ( IPCMAX .GT. 1 ) 1 CALL ENINT (V1/SPDSND, APA+HT, XTT, XFF, 1, TMAX, ITD, 1 ) TTM(IA) = THRU / TMAX WT(IA) = WT(IA-1) - DELT * (FF + FFO) * NE / 7200. FFO = FF TTO = TTOO CLL(IA) = CL + DCL CDD(IA) = CDG + CDGR + CDP ALT(IA) = HT GAM(IA) = GAMFLT ACL(IA) = ACC IF ( IL .LT. 10 ) GO TO 160 C OBSTACLE HAS BEEN REACHED KA(ISEG) = IA IF ( IPRINT .GT. 0 ) WRITE(IU6, 630) KEY, T(IA), ALT(IA), D(IA), 1 V(IA)/SPD, GAM(IA), ALP(IA), WT(IA), FLAPA(IA), CLL(IA), 2 CLL(IA)/CDD(IA), FLOAT(IGR(IA)), TH(IA), ZERO, TTM(IA) C POST-OBSTACLE CLIMB SEGMENTS 250 ISEG = ISEG + 1 ICUT = 0 VE = V(IA) DE = D(IA) TI = T(IA) ALPH1 = ALP(IA) GAMFLT = GAM(IA) VVERT = VE * SIN(GAMFLT*RAD) VHORZ = VE * COS(GAMFLT*RAD) HT = ALT(IA) IFP = IFLP(ISEG) DELT = DLT(ISEG) VSTOP = VSTP(ISEG) * SPD IF ( VSTP(ISEG) .GT. 0. .AND. VSTP(ISEG) .LE. 50. ) 1 VSTOP = MAX(VE,(VEE2+VSTP(ISEG))*SPD) DSTOP = DSTP(ISEG) TSTOP = TSTP(ISEG) HSTOP = HSTP(ISEG) HMIN = HMN(ISEG) KEY = KEYS(ISEG) IF ( KEY .EQ. 'CUTB' ) GO TO 740 IF ( ENGSC(ISEG) .GT. 0. ) ENGSCL = ENGSC(ISEG) C IFIX = 1, FIXED THRUST AND CONSTANT VELOCITY C = 2, FIXED THRUST AND CONSTANT FLIGHT PATH ANGLE C = 3, FIXED THRUST AND FIXED ANGLE OF ATTACK C = 4, FIXED VELOCITY AND CONSTANT FLIGHT PATH ANGLE C = 5, FIXED THRUST AND FIXED FLOOR ANGLE (ALPHA + GAMMA) GO TO ( 260, 270, 280, 285, 275, 500 ) IFX(ISEG) 260 VFIX = VFX(ISEG) * SPD IF ( VFX(ISEG) .LE. 50. ) VFIX = MAX(VE,(VEE2+VFX(ISEG))*SPD) IF ( VFX(ISEG) .LE. 0. ) VFIX = VE VE = VFIX GO TO 290 270 GFIX = GFX(ISEG) IF ( GFIX .LE. 0. ) GFIX = GAMFLT GAMFLT = GFIX GO TO 290 275 GFIX = GFX(ISEG) IF ( GFIX .LE. 0. ) GFIX = GAMFLT + ALPH1 GAMFLT = GFIX - ALPH1 GO TO 290 280 AFIX = AFX(ISEG) IF ( AFIX .LE. 0. ) AFIX = ALPH1 GO TO 290 285 VFIX = VFX(ISEG) * SPD IF ( VFX(ISEG) .LE. 50. ) VFIX = (VEE2 + VFX(ISEG)) * SPD IF ( VFX(ISEG) .LE. 0. ) VFIX = VE VE = VFIX GFIX = GFX(ISEG) IF ( GFIX .LE. 0. ) GFIX = GAMFLT 287 GAMFLT = GFIX DELFO = 0. ACCH = 0. 290 ISTOP = 0 IFIX = IFX(ISEG) IF ( IFIX .EQ. 4 ) THEN GFIX = GFX(ISEG) GAMFLT = GFIX ENDIF ALPOL = ALPH1 294 GAMP = GFIX TVO = V1 295 M = 0 DELTAL = VANGL * DELT ALPAT = ALPH1 + DELTAL ALPIT = ALPH1 - DELTAL IF ( ALPAT .GT. ALMXTO ) ALPAT = ALMXTO IF ( ALPIT .LT. ALPMIN ) ALPIT = ALPMIN IF ( IFIX .EQ. 3 ) ALPH1 = AFIX 300 IF ( ALPH1 .GT. ALPAT .AND. ICUT .EQ. 0 ) ALPH1 = ALPAT IF ( ALPH1 .LT. ALPIT .AND. ICUT .EQ. 0 ) ALPH1 = ALPIT 305 DELTAV = DELT * ACC V1 = VE + DELTAV IF ( IFIX .EQ. 1 .OR. IFIX .EQ. 4 ) V1 = VFIX DELTLP = ALPH1 - ALPRUN HO = HT + DELT * VVERT CALL ATMO ( APA+HO, DTCT, DELTA, THETA, ASTAR, TM, RE, HFT ) SPDSND = ASTAR * SPD RHOA = 0.0023769 * SW * DELTA / THETA / 2. CALL GEFECT (ALPH1, HO, GAMFLT, ALPRO(1,IFP), CLPRO(1,IFP), 1 CDPRO(1,IFP), CDMTO, CL, CDG, ARRET*ARGEF, WHGT, SPAN ) C INCLUDE GEAR DRAG IF IT IS STILL DOWN CDGR = 0.0 IF ( (TI + DELT - TLO) .LE. TIGEAR .AND. TIGEAR .GT. 0. ) 1 CDGR = CDGEAR * COS( ((TI + DELT - TLO) / TIGEAR) * 90.0 * RAD ) IGER = 0 IF ( CDGR .GT. 0. ) IGER = 1 CDP = XINT1 ( V1, VELTO, 10, CDDP ) CDEO = 0. IF ( ICUT .EQ. 2 ) CDEO = CDEOUT DRAG = (CDG + CDP + CDGR + CDEO) * V1**2 * RHOA CLP = XINT1 ( V1, VELTO, 10, CLDPOC ) DCL = CLP / CL CLIFT = (CL + DCL) * V1**2 * RHOA CG = COS( GAMFLT * RAD ) SG = SIN( GAMFLT * RAD ) IF ( IFIX .EQ. 4 ) GO TO 720 THRU = ENGSCL DESP = DELT*SPRT(ISEG) IF ( ABS(THRU-TTO) .GT. DESP .AND. DESP .GT. 0. ) THEN IF ( THRU .GT. TTO ) THRU = TTO + DESP IF ( THRU .LT. TTO ) THRU = TTO - DESP ENDIF TTOO = THRU CALL ENINT ( V1/SPDSND, APA+HO, THRU, FF, 2, TMAX, ITD, IPCMAX ) CWT = WT(IA) - DELT * (FF + FFO) * NE / 7200. TNETH = THRU * NE * COS( (TINC + DELTLP + GAMFLT) * RAD ) TNETV = THRU * NE * SIN( (TINC + DELTLP + GAMFLT) * RAD ) FORCH = TNETH - CLIFT * SG - DRAG * CG FORCV = TNETV + CLIFT * CG - CWT - DRAG * SG ACCH = FORCH * G / CWT ACCV = FORCV * G / CWT HO = HT + DELT * (VVERT + DELT * ACCV / 2.0 ) TVERT = VVERT + DELT * ACCV THORZ = VHORZ + DELT * ACCH TV = SQRT(TVERT**2 + THORZ**2) GAMFLT = ATAN(TVERT / THORZ) / RAD ACC = (ACCH * THORZ + ACCV * TVERT ) / TV M = M + 1 IF ( (M - 2*(M/2)) .GT. 0 ) GO TO 300 IF ( IFIX .EQ. 2 ) GO TO 310 IF ( IFIX .EQ. 5 ) GO TO 315 IF ( IFIX .EQ. 1 ) GO TO 308 IF ( GAMFLT .GE. GAMLIM ) GO TO 320 GFIX = GAMLIM 307 ISTOP = 0 IFIX = 2 GAMFLT = GFIX ALPH1 = ALP(IA) ALPOL = ALPH1 GO TO 294 308 ERRMOD = VFIX - TV IF ( ACC .GT. 0.1 ) ERRMOD = ERRMOD - ACC*DELT/2. IF ( ABS(ERRMOD) .LE. .001 ) GO TO 309 IF ( TV .GT. VFIX .AND. ALPH1 .GE. ALPAT ) GO TO 309 IF ( TV .LT. VFIX .AND. ALPH1 .LE. ALPIT ) GO TO 309 DELTAL = SIGN (VANGL*DELT/10, -ERRMOD) DTV = TV - TVO DTEST = DTV * (ALPH1-ALPOL) IF ( M .GT. 2 .AND. ABS(DTV) .GT. .001 .AND. DTEST .LT. 0. ) 1 DELTAL = ERRMOD * (ALPH1-ALPOL) / DTV ALPOL = ALPH1 TVO = TV ALPH1 = ALPH1 + DELTAL IF ( M .LT. 20) GO TO 300 309 GAMT = 0.5 * (GAM(IA) - GAMLIM) IF ( GAM(IA)-GAMFLT .GT. GAMT .AND. GAMT .GT. 0.1 ) THEN GFIX = GAM(IA) - GAMT GO TO 307 ELSE IF ( GAMFLT .LT. GAMLIM ) THEN GFIX = GAMLIM GO TO 307 ENDIF GO TO 320 310 IF ( ABS(GAMFLT-GFIX) .LE. .001 ) GO TO 320 IF ( GAMFLT .LT. GFIX .AND. ALPH1 .GE. ALPAT ) GO TO 320 IF ( GAMFLT .GT. GFIX .AND. ALPH1 .LE. ALPIT ) GO TO 320 DELTAL = SIGN (.1,(GFIX-GAMFLT)) DGM = GAMFLT - GAMP IF ( M .GT. 2 .AND. ABS(DGM) .GT. .001 ) 1 DELTAL = (GFIX-GAMFLT) * (ALPH1-ALPOL) / DGM ALPOL = ALPH1 GAMP = GAMFLT ALPH1 = ALPH1 + DELTAL IF ( M .LT. 20) GO TO 300 GO TO 320 315 GAMFLO = GAMFLT + ALPH1 IF ( ABS(GAMFLO-GFIX) .LE. .001 ) GO TO 320 IF ( GAMFLO .LT. GFIX .AND. ALPH1 .GE. ALPAT ) GO TO 320 IF ( GAMFLO .GT. GFIX .AND. ALPH1 .LE. ALPIT ) GO TO 320 DELTAL = SIGN (.1D0,(GFIX-GAMFLO)) DGM = GAMFLO - GAMP IF ( M .GT. 2 .AND. ABS(DGM) .GT. .001 ) 1 DELTAL = (GFIX-GAMFLO) * (ALPH1-ALPOL) / DGM ALPOL = ALPH1 GAMP = GAMFLO ALPH1 = ALPH1 + DELTAL IF ( M .LT. 20) GO TO 300 GO TO 320 720 ALPNU = (DELTLP + TINC) * RAD CWT = WT(IA) - DELT * FFO * NE / 3600. SAU = SIN(ALPNU) CAU = COS(ALPNU) FH = DRAG + CWT * SG FV = CWT * CG - CLIFT DELFF = FH * SAU - FV * CAU M = M + 1 IF ( ABS(DELFF) .LT. .00001*GROSWT .OR. M .GE. 20 ) GO TO 730 DELA = - SIGN(.1D0,DELFF) DDELF = DELFF - DELFO IF ( M .GT. 1 .AND. ABS(DDELF) .GT. 1. ) 1 DELA = DELFF * (ALPO - ALPH1) / DDELF IF ( ABS(DELA) .GT. 1. ) DELA = SIGN(1.D0,DELA) IF ( ABS(DELA) .LT. .0001 ) GO TO 730 ALPO = ALPH1 DELFO = DELFF ALPH1 = ALPH1 + DELA GO TO 305 730 THRU = (FH/CAU + FV/SAU) / (2. * NE) IF ( ICUT .GT. 0 ) GO TO 750 CALL ENINT (V1/SPDSND, APA+HO, THRU, FF, 2, TMAX, ITD, IPCMAX) ENGSCL = THRU / TMAX DESP = DELT*SPRT(ISEG) IF ( ( ABS(ENGSCL-TTO) .LT. DESP .OR. DESP .LE. 0. ) .AND. 1 ( THRU .LE. TMAX ) ) THEN IF ( ALPH1 .LT. ALPIT ) THEN ALPH1 = ALPIT IFIX = 3 GO TO 305 ELSE IF ( ALPH1 .GT. ALPAT ) THEN ALPH1 = ALPAT IFIX = 3 GO TO 305 ENDIF TV = V1 ACC = (TV - TVO) / DELT TVERT = TV * SG THORZ = TV * CG ACCV = (TVERT - VVERT) / DELT ACCH = (THORZ - VHORZ) / DELT HO = HT + DELT * (VVERT + DELT * ACCV / 2.0 ) TVO = TV GO TO 320 ELSE IFIX = 1 ALPH1 = ALPOL GO TO 295 ENDIF 740 IFX(ISEG) = 4 GFX(ISEG) = GRAEO(ISEG) VFIX = VE ICUT = 1 DELT = 0. GO TO 287 750 IF ( ICUT .EQ. 2 ) GO TO 760 TREQ1 = THRU TREQ2 = 0. GFX(ISEG) = GROEO(ISEG) IF ( NE .GT. 1 ) THEN ICUT = 2 GO TO 287 ENDIF 760 IF ( NE .GT. 1 ) TREQ2 = NE * THRU / (NE - 1) TREQ = MAX(TREQ1,TREQ2) CALL ENINT (VE/SPDSND, APA+HO, TT, FF, 1, TMAX, ITD, IPCMAX) ENGSCL = TREQ / TMAX IF ( TMAX .LT. TREQ ) THEN IF ( IPRINT .GT. 0 ) WRITE(IU6, 790) 790 FORMAT (/' INSUFFICIENT THRUST AVAILABLE AT CUTBACK') IF ( IPCMAX .EQ. 1 ) ENGSC(ISEG+1) = 1. ENDIF IF ( IPRINT .GT. 0 ) WRITE(IU6, 810) ENGSCL, TREQ1, TREQ2 810 FORMAT ( ' CUTBACK SEGMENT - NEW ENGINE SETTING =',F8.5, 1 ', THRUST REQUIRED =',F9.1,' (AEO) OR',F9.1,' (OEO)') GO TO 250 320 HT = HO DE = DE + DELT * (VHORZ + ACCH * DELT / 2.0) VVERT = TVERT VHORZ = THORZ VE = TV TI = TI + DELT IA = IA + 1 IF ( IA .GT. 500 ) GO TO 500 T(IA) = TI D(IA) = DE V(IA) = VE ALP(IA) = ALPH1 WT(IA) = CWT FLAPA(IA) = DFLAP(IFP) IGR(IA) = IGER TH(IA) = THRU * NE IF ( IPCMAX .GT. 1 ) 1 CALL ENINT (VE/SPDSND, APA+HO, XTT, XFF, 1, TMAX, ITD, 1 ) TTM(IA) = THRU / TMAX WT(IA) = WT(IA-1) - DELT * (FF + FFO) * NE / 7200. FFO = FF CLL(IA) = CL + DCL CDD(IA) = CDG + CDGR + CDP ALT(IA) = HT GAM(IA) = GAMFLT ACL(IA) = ACC C CHECK FOR END OF SEGMENT DL = 0. IF ( HSTOP .LE. 0. .OR. ALT(IA) .LT. HSTOP ) GO TO 330 DL = (ALT(IA) - HSTOP) / (ALT(IA) - ALT(IA-1)) ISTOP = 1 330 IF ( DSTOP .LE. 0. .OR. D(IA) .LT. DSTOP ) GO TO 340 IF ( ALT(IA) .GE. HMIN .OR. HMIN .LE. 0. ) GO TO 335 HSTOP = HMIN DSTOP = DSTOP * 10. GO TO 340 335 DLP = (D(IA) - DSTOP) / (D(IA) - D(IA-1)) DL = MAX(DL,DLP) ISTOP = 1 340 IF ( TSTOP .LE. 0. .OR. T(IA) .LT. TSTOP ) GO TO 350 IF ( ALT(IA) .GE. HMIN .OR. HMIN .LE. 0. ) GO TO 345 HSTOP = HMIN TSTOP = TSTOP * 10. GO TO 350 345 DLP = (T(IA) - TSTOP) / (T(IA) - T(IA-1)) DL = MAX(DL,DLP) ISTOP = 1 350 IF ( VSTOP .LE. 0. .OR. V(IA) .LT. VSTOP ) GO TO 360 IF ( ALT(IA) .GE. HMIN .OR. HMIN .LE. 0. ) GO TO 355 HSTOP = HMIN VSTOP = VSTOP * 10. GO TO 360 355 DLP = (V(IA) - VSTOP) / (V(IA) - V(IA-1)) DL = MAX(DL,DLP) ISTOP = 1 360 IF ( ISTOP .EQ. 0 ) THEN TTO = TTOO GO TO 290 ENDIF V(IA) = (1. - DL) * V(IA) + DL * V(IA-1) T(IA) = (1. - DL) * T(IA) + DL * T(IA-1) D(IA) = (1. - DL) * D(IA) + DL * D(IA-1) ALT(IA) = (1. - DL) * ALT(IA) + DL * ALT(IA-1) WT(IA) = (1. - DL) * WT(IA) + DL * WT(IA-1) ALP(IA) = (1. - DL) * ALP(IA) + DL * ALP(IA-1) GAM(IA) = (1. - DL) * GAM(IA) + DL * GAM(IA-1) CLL(IA) = (1. - DL) * CLL(IA) + DL * CLL(IA-1) CDD(IA) = (1. - DL) * CDD(IA) + DL * CDD(IA-1) TH(IA) = (1. - DL) * TH(IA) + DL * TH(IA-1) TTM(IA) = (1. - DL) * TTM(IA) + DL * TTM(IA-1) ACL(IA) = (1. - DL) * ACL(IA) + DL * ACL(IA-1) TTO = (1. - DL) * TTOO + DL * TTO KA(ISEG) = IA IF ( IPRINT .GT. 0 ) WRITE(IU6, 630) KEY, T(IA), ALT(IA), D(IA), 1 V(IA)/SPD, GAM(IA), ALP(IA), WT(IA), FLAPA(IA), CLL(IA), 2 CLL(IA)/CDD(IA), FLOAT(IGR(IA)), TH(IA), ZERO, TTM(IA) IF ( KEY .EQ. 'CHAN' ) GO TO 250 C OUTPUT DETAILED RESULTS 510 IF ( NTIME .NE. 1 .OR. IPRINT .LE. 0 ) GO TO 610 WRITE(IU6, 570) 570 FORMAT (/' COUNT TIME HEIGHT DISTANCE SPEED GAMMA', 1 ' ALPHA WEIGHT FLAPS CL L/D EGEAR THRUST', 2 ' VJET T/TMAX' ) I1 = 1 DO 600 N = 1,NSEG IF ( KEYS(N) .EQ. 'CUTB' ) GO TO 600 I2 = KA(N) WRITE(IU6, 580) 580 FORMAT (5X) WRITE(IU6, 590) (I, T(I), ALT(I), D(I), V(I)/SPD, GAM(I), ALP(I), 1 WT(I), FLAPA(I), CLL(I), CLL(I)/CDD(I), 2 FLOAT(IGR(I)), TH(I), ZERO, TTM(I), I = I1,I2) 590 FORMAT (I6,F8.2,F9.2,F10.1,3F8.2,F10.0,F7.1,F9.4,F8.2,F7.1,F10.1, 1 F7.1,F9.4) I1 = I2 + 1 600 CONTINUE 630 FORMAT (2X,A4,F8.2,F9.2,F10.1,3F8.2,F10.0,F7.1,F9.4,F8.2,F7.1, 1 F10.1,F7.1,F9.4) 610 IF ( NPFILE .NE. 1 ) RETURN WRITE(IU9, 590) (I, T(I), ALT(I), D(I), V(I)/SPD, GAM(I), ALP(I), 1 WT(I), FLAPA(I), CLL(I), CLL(I)/CDD(I), 2 FLOAT(IGR(I)), TH(I), ZERO, TTM(I), I = 1,IA) IF ( IXFL .EQ. 1 ) RETURN I = IA N = 999 WRITE(IU9, 590) N, T(I), ALT(I), D(I), V(I)/SPD, GAM(I), ALP(I), 1 WT(I), FLAPA(I), CLL(I), CLL(I)/CDD(I), 2 FLOAT(IGR(I)), TH(I), ZERO, TTM(I) RETURN 500 WRITE(IU6, 505) 505 FORMAT (/' * * FAILURE IN DETAILED TAKEOFF AND CLIMBOUT,', 1 ' PROFILE CALCULATIONS TERMINATED * *') GO TO 510 550 FORMAT (' * * ITERATION OF LIFTOFF VELOCITY IS INCOMPLETE * *',/ 1(I5,6H DELT=,F7.3,8H DELFOR=,F10.2,7H ALPHA=,F7.3,6H HFOR=,F9.2)) END