1 SUBROUTINE TRIMRT 2C 3C*** CALCULATES SUBSONIC TRIM WITH WING OR HORIZONTAL TAIL CONTROL 4C 5 COMMON /OVERLY/ NLOG,NMACH,IZ,NALPHA 6 COMMON /FLAPIN/ F(69) 7 COMMON /IHT/ PHT, HT(380) 8 COMMON /IVT/ PVT, VT(380) 9 COMMON /IDWASH/ PDWASH, DWASH(60) 10 COMMON /IWING/ PWING, WING(400) 11 COMMON /IBODY/ PBODY, BODY(400) 12 COMMON /WINGD/ A(195),B(49) 13 COMMON /HTDATA/ AHT(195),BHT(49) 14 COMMON /POWR/ PW(293),TRM(22) 15 COMMON /IBW/ PBW, BW(380) 16 COMMON /IBWH/ PBWH, BWH(380) 17 COMMON /IBWHV/ PBWHV, BWHV(380) 18 COMMON /FLGTCD/ FLC(93) 19 COMMON /FLOLOG/ FLTC,OPTI,BO,WGPL,WGSC,SYNT,HTPL,HTSC,VTPL,VTSC, 20 1 HEAD,PRPOWR,JETPOW,LOASRT,TVTPAN,SUPERS,SUBSON, 21 2 TRANSN,HYPERS,SYMFP,ASYFP,TRIMC,TRIM,DAMP, 22 3 HYPEF,TRAJET,BUILD,FIRST,DRCONV,PART, 23 4 VFPL,VFSC,CTAB 24C 25 LOGICAL FLTC,OPTI,BO,WGPL,WGSC,SYNT,HTPL,HTSC,VTPL,VTSC, 26 1 HEAD,PRPOWR,JETPOW,LOASRT,TVTPAN,SUPERS,SUBSON, 27 2 TRANSN,HYPERS,SYMFP,ASYFP,TRIMC,TRIM,DAMP, 28 3 HYPEF,TRAJET,BUILD,FIRST,DRCONV,PART, 29 4 VFPL,VFSC,CTAB 30 REAL NTRIM 31 DIMENSION UTCL(20),UTCM(20),UTCD(20),ALPHA(20),DCM(10),DCL(10), 32 1 DCLMAX(10),DCDMIN(10),CHD(10),CDI(200) 33 DIMENSION DELTA(10) 34 DIMENSION DCM2(10),DELT(10),ROUTID(2) 35 DIMENSION C1(6),C2(6),C3(6),C4(6),C5(6) 36 DIMENSION DELTAT(20),DCLT(20),CLMAXT(20),CDMINT(20),CHDT(20), 37 1 CDIT(20) 38 EQUIVALENCE (UTCL(1),HT(201)),(UTCM(1),HT(241)),(UTCD(1),HT(221)) 39 1 ,(ALPHA(1),TRM(1)),(DELTAT(1),VT(201)),(DCLT(1),VT(221)) 40 2 ,(CLMAXT(1),VT(241)),(CDMINT(1),VT(281)),(CHDT(1),VT(321)) 41 3 ,(CDIT(1),VT(261)),(NTRIM,TRM(21)) 42 EQUIVALENCE (TSTOP,TRM(22)) 43 EQUIVALENCE (DELTA(1),F(1)) 44 EQUIVALENCE (DCM(1),WING(211)),(DCL(1),WING(201)) 45 1,(DCDMIN(1),WING(231)),(CHD(1),WING(261)),(CDI(1),BODY(201)) 46 2,(DCLMAX(1),WING(221)) 47 DATA ROUTID/4HTRIM,4HRT / 48C 49 IN=0 50 I1=0 51 I2=0 52 I3=0 53 I4=0 54C 55C -----TRIM HERE WITH CONTROL DEVICE ON WING OR TAIL 56C 57 NDELTA=F(16)+.5 58 NDELTA = NDELTA - 1 59 IF(WGPL.AND.HTPL)GO TO 1030 60 IF(BO)GO TO 1010 61C 62C -----HERE FOR WING ALONE TRIM 63C 64 DO 1000 J=1,NALPHA 65 UTCL(J)=WING(J+20) 66 UTCM(J)=WING(J+40) 67 1000 UTCD(J)=WING(J) 68 ACLMAX=B(43) 69 GO TO 1050 70C 71C -----HERE FOR WING-BODY TRIM 72C 73 1010 DO 1020 J=1,NALPHA 74 UTCL(J)=BW(J+20) 75 UTCM(J)=BW(J+40) 76 1020 UTCD(J)=BW(J) 77 ACLMAX=B(43) 78 GO TO 1050 79C 80C -----HERE FOR WING-BODY-TAIL TRIM 81C 82 1030 DO 1040 J=1,NALPHA 83 UTCL(J)=BWH(J+20) 84 UTCM(J)=BWH(J+40) 85 UTCD(J)=BWH(J) 86 IF(VTPL .OR. VFPL) UTCD(J)=BWHV(J) 87 1040 CONTINUE 88 ACLMAX=BHT(43) 89 1050 CONTINUE 90 NTRIM=NALPHA 91 IF(DCM(1).GT.DCM(NDELTA))GO TO 1070 92 DO 1060 J=1,NDELTA 93 DELT(J)=DELTA(J) 94 1060 DCM2(J)=DCM(J) 95 GO TO 1090 96 1070 DO 1080 J=1,NDELTA 97 N=NDELTA-J+1 98 DELT(N)=DELTA(J) 99 1080 DCM2(N)=DCM(J) 100 1090 DO 1100 J=1,NALPHA 101 ALPHA(J)=FLC(J+22)-DWASH(J+20) 102 1100 CONTINUE 103 DO 1130 J=1,NALPHA 104 IF(ALPHA(J).GT.ACLMAX)GO TO 1110 105 ARG=-UTCM(J) 106 IF(ARG.LT.DCM2(1).OR.ARG.GT.DCM2(NDELTA))GO TO 1120 107 CALL TBFUNX(ARG,DELTAT(J),DYDX,NDELTA,DCM2,DELT,C1,IN,MI,NG 108 1 ,0,0,4HDELT,1,ROUTID) 109 CALL TBFUNX(DELTAT(J),DCLT(J),DYDX,NDELTA,DELTA,DCL,C2,I2, 110 1 MI,NG,0,0,4HDCLT,1,ROUTID) 111 IF(F(17).LE.5.)CALL TBFUNX(DELTAT(J),CLMAXT(J),DYDX,NDELTA, 112 1 DELTA,DCLMAX,C3,I3,MI,NG,0,0,4HCLMT,1,ROUTID) 113 IF(F(17).LE.2.)CALL TBFUNX(DELTAT(J),CDMINT(J),DYDX,NDELTA, 114 1 DELTA,DCDMIN,C4,I4,MI,NG,0,0,4HCDMT,1,ROUTID) 115 IF(F(17).EQ.1.)CALL TBFUNX(DELTAT(J),CHDT(J),DYDX,NDELTA,DELTA, 116 1 CHD,C5,I5,MI,NG,0,0,4HCHDT,1,ROUTID) 117 IF(F(17).LE.6.)CALL TLINEX(DELTA,ALPHA,CDI,NDELTA,NALPHA 118 1 ,DELTAT(J),ALPHA(J),CDIT(J),0,0,0,0,4HCDIT,1,ROUTID) 119 GO TO 1130 120 1110 NTRIM=J-1 121 TSTOP=2. 122 GO TO 1140 123 1120 NTRIM=J-1 124 TSTOP=1. 125 GO TO 1140 126 1130 CONTINUE 127 1140 CONTINUE 128 RETURN 129 END 130