1 SUBROUTINE SUPLAF 2C 3C*** SUPERSONIC VENTRAL FIN LATERAL STABILITY 4C 5 COMMON /IVF/ PVT, VT(380) 6 COMMON /IBW/ PBW, BWI(380) 7 COMMON /IBWV/ PBWV, BWV(380) 8 COMMON /IBWHV/ PBWHV, BWHV(380) 9C 10 COMMON /FLGTCD/ FLC(160) 11 COMMON /OPTION/ SREF, CBARR, ROUGFC, BLREF 12 COMMON /SYNTSS/ XCG, XW, ZW, ALIW, ZCG, XH, ZHH, ALIH, XV, 13 1 VERTUP, HINAX, XVF, SC, ZV, ZVF, YV, YF, 14 2 PHIV, PHIF 15 COMMON /WINGI/ WINGIN(101) 16 COMMON /VTI/ VV(162), VTIN(154) 17 COMMON /HTI/ HTIN(154) 18 COMMON /SBETA/ SSS(31), SLA(31) 19 COMMON /HTDATA/ AHT(195), BHT(49) 20 COMMON /VTDATA/ AAA(195), AVT(195) 21 COMMON /CONSNT/ PI,DEG,UNUSED,RAD,KAND 22 COMMON /OVERLY/ NLOG,NMACH,I,NALPHA,IG,NF,LF,K 23 COMMON /FLOLOG/ FLTC,OPTI,BO,WGPL,WGSC,SYNT,HTPL,HTSC,VTPL,VTSC, 24 1 HEAD,PRPOWR,JETPOW,LOASRT,TVTPAN,SUPERS,SUBSON, 25 2 TRANSN,HYPERS,SYMFP,ASYFP,TRIMC,TRIM,DAMP, 26 3 HYPEF,TRAJET,BUILD,FIRST,DRCONV,PART, 27 4 VFPL,VFSC,CTAB 28C 29 LOGICAL FLTC,OPTI,BO,WGPL,WGSC,SYNT,HTPL,HTSC,VTPL,VTSC, 30 1 HEAD,PRPOWR,JETPOW,LOASRT,TVTPAN,SUPERS,SUBSON, 31 2 TRANSN,HYPERS,SYMFP,ASYFP,TRIMC,TRIM,DAMP, 32 3 HYPEF,TRAJET,BUILD,FIRST,DRCONV,PART, 33 4 VFPL,VFSC,CTAB 34 LOGICAL VHPLA, VERTUP 35C 36 DIMENSION ROUTID(2), QAMF(3), XAMF(3), YAMF(3), CC(6) 37 DIMENSION ALPHA(20), SYNA(19) 38 DIMENSION RLPH(20), SVB(20), SVWB(20), SVHB(20) 39C 40 EQUIVALENCE (ALPHA(1),FLC(23)) 41 EQUIVALENCE (DCVWHB,VT(141)), (DCYHWB,SLA(23)) 42 EQUIVALENCE (RKVWB,SLA(24)), (RKVB,SLA(25)), (RKPVWB,SLA(26)) 43 EQUIVALENCE (DCYBV,SLA(27)), (RKVHB,SLA(28)), (ZP,SLA(29)) 44 EQUIVALENCE (RLP,SLA(30)), (CNAV,SLA(31)) 45 EQUIVALENCE (SYNA(1),XCG), (SPAN,WINGIN(4)) 46 EQUIVALENCE (RLPH(1),HTIN(95)), (SVWB(1),VTIN(95)) 47 EQUIVALENCE (SVB(1),VTIN(115)), (SVHB(1),VTIN(135)) 48C 49 DATA WTYPE / 4HSTRA / 50 DATA ROUTID / 4HSUPL, 4HAF / 51 DATA QAMF / 4H5.3., 4H1.1-, 4H25A / 52 DATA XAMF / 0.0, 0.40, 1.0 / 53 DATA YAMF / 0.5, 1.79, 4.0 / 54C 55 ZH = ZHH-((HTIN(4)-HTIN(3))*AHT(62)+AHT(30))*SIN(ALIH/RAD) 56 SVSTAR = AVT(3) 57 VHPLA = .FALSE. 58 SCALE = 2.0*SPAN/BLREF 59C 60C ***VERTICAL TAIL ADDED TO WING-BODY*** 61C 62 R1=VTIN(4)-VTIN(3) 63 R1OBA=R1/VTIN(4) 64 R2OBO2=R1/WINGIN(4) 65 ZHOR1=-ZW/R1 66 1000 IF(VERTUP)ZHOR1=-ZHOR1 67C 68C CALL SUBROUTINE MASRAT FOR FIG.5.3.1.1-25B-P 69C 70 CALL MASRAT(R2OBO2,R1OBA,ZHOR1,ARG1) 71 IF(VHPLA)GO TO 1010 72C 73C FIGURE 5.3.1.1-25A KV(B) 74C 75 IN = 0 76 CALL TBFUNX(R1OBA, RKVB, DYDX, 3, XAMF, YAMF, CC, 77 1 IN, MI, NG, 0, 1, QAMF, 3, ROUTID) 78 RKVWB=ARG1 79 RKPVWB= (RKVB*SVB(I)+RKVWB*SVWB(I))/SVSTAR 80 DCYBV=-RKPVWB*CNAV 81C 82C ***VERTICAL PANEL ADDED TO WING-BODY-HORIZONTAL TAIL*** 83C 84 IF(.NOT. HTPL) GO TO 1020 85 R2OBO2=R1/HTIN(4) 86 ZHOR1=ZH/R1 87 VHPLA=.TRUE. 88 GO TO 1000 89 1010 RKVHB=ARG1 90 DCVWHB=DCYBV-RKVHB*SVHB(I)/SVSTAR*CNAV 91 1020 CONTINUE 92C 93C *** WING-BODY-TAIL DERIVATIVES *** 94C 95 BW=2.*SPAN 96 DELX=AVT(62)*(VTIN(4)-VTIN(3)) 97 RLP=SYNA(9)-SYNA(1)+DELX+AVT(30) 98 ZP=-SYNA(5)+VTIN(4)-VTIN(3)+AVT(31)+SYNA(14) 99 VT(141) = DCYBV 100 VT(161) = -DCYBV*RLP/BLREF 101 BWV(141) = BWV(141)+VT(141) 102 BWV(161) = BWV(161)+VT(161) 103 IF(WINGIN(15).NE.WTYPE) GO TO 1050 104 DO 1030 J=1,NALPHA 105 ALP=ALPHA(J)/RAD 106 DZ=(ZP*COS(ALP)-RLP*SIN(ALP))/BW 107 BWV(J+180)=BWV(J+180)+DCYBV*DZ*SCALE 108 1030 CONTINUE 109 IF(.NOT. HTPL) GO TO 1050 110 BWHV(141)=BWHV(141)+DCVWHB 111 BWHV(161)=BWHV(161)-DCVWHB*RLP/BLREF 112 DO 1040 J=1,NALPHA 113 ALP=ALPHA(J)/RAD 114 DZ=(ZP*COS(ALP)-RLP*SIN(ALP))/BW 115 VT(J+180) = DCVWHB*DZ*SCALE 116 BWHV(J+180)=BWHV(J+180)+VT(J+180) 117 1040 CONTINUE 118 1050 CONTINUE 119 RETURN 120 END 121