1 SUBROUTINE SUPWB 2C 3C*** CALCULATES SUPERSONIC WING-BODY AERO 4C 5 REAL MACH,NXX,KWB,KBW,IVBW ,KKBW,KKWB 6 DIMENSION ROUTID(2),Q1211A(3),Q1211B(3),Q31210(3),Q1212A(3), 7 1 Q1212B(3),Q2118A(3),Q2118B(3),Q2137A(3),Q2137B(3) 8 DIMENSION T4312B(8),D4312B(8) 9 DIMENSION CDW(20),CDB(20),WTYPE(4),IVBW(20),GAMMA(20) 10 DIMENSION T4337A(11),D4337A(24),T4337B(12),D4337B(20) 11 DIMENSION T4312A(11),D4312A(11) 12 DIMENSION TFIG10(11),DKWB10(11),DKBW10(11) 13 DIMENSION T4218A(18),DL218A(54),DR218A(54),T4218B(14),DL218B(42), 14 1 DR218B(42) 15 DIMENSION LGH(4),VAR(4),CD(20),CN(20),CA(20),CL(20),CLB(20), 16 1 CLW(20),ALPHAB(20),CDL(20) 17 DIMENSION CM(20) 18C 19 COMMON /CONSNT/ PI,DEG,UNUSED,RAD 20 COMMON /FLGTCD/ FLC(160) 21 COMMON /SYNTSS/ SYNA(19) 22 COMMON /OPTION/ SREF,CBARR,ROUGFC,BLREF 23 COMMON /WINGI/ W(2),SPANS,SPAN,W1,CR,W2(8),TYPE 24 COMMON /BODYI/ NXX,XCOOR(20),S(20),P(20),R(20),ZU(20),ZL(20), 25 1 BNOSE,BTAIL,RLN 26 COMMON /BDATA/ BD(762) 27 COMMON /WINGD/ A(195) 28 COMMON /OVERLY/ NLOG,NMACH,I,NALPHA 29 COMMON /SUPBOD/ SBD(229) 30 COMMON /SUPWBB/ SWB(61) 31 COMMON /SUPWH/ SLG(141) 32 COMMON /IBODY/ PBODY, BODY(400) 33 COMMON /IWING/ PWING, WING(400) 34 COMMON /IBW/ PBW, BW(380) 35C 36 EQUIVALENCE (CA(1),BW(81)),(CDW(1),WING(1)),(CMA,BW(121)), 37 1 (DXCG,A(173)),(CLAB,SBD(18)),(KKWB,SWB(2)), 38 2 (XACN,SWB(3)),(CDOWB,SWB(4)),(DELXW,BD(66)),(ARSTAR,A(7)), 39 3 (CD(1),BW(1)),(DD,SWB(5)),(XW,SYNA(2)),(CLB(1),BODY(21)), 40 4 (ALIW,SYNA(4)),(BETA,SWB(6)),(CLAW,WING(101)), 41 5 (XACW,SLG(134)),(CLABW,SWB(7)) ,(XACBW,SWB(8)) 42 EQUIVALENCE (CLA,BW(101)),(CDL(1),SLG(53)) 43 EQUIVALENCE (CL(1),BW(21)),(FA,SWB(9)),(CLI,SWB(10)), 44 1 (KBW,SWB(11)),(CDOB,SBD(124)),(IVBW(1),SWB(12)),(RKBW,SWB(32)), 45 2 (CLAWB,SWB(33)),(TANL ,A(62)),(CRSTAR,A(10)), 46 3 (TAPEXP,A(27)),(CN(1),BW(61)),(FN, SWB(34)),(CDB(1),BODY(1)), 47 4 (CLW(1),WING(21)),(KWB,SWB(35)),(XAC,SWB(36)) ,(CDOW,SLG(80)), 48 5 (DN,SBD(4)),(D1,SBD(5)),(KKBW,SWB(37)),(RLAP,SWB(38)) 49 EQUIVALENCE (XACA,SWB(39)),(GAMMA(1),SWB(40)), 50 1 (TRINO,SWB(60)),(XCPLN,SWB(61)),(ALPHAB(1),BD(255)) 51 2 ,(CM(1),BW(41)) 52C 53 DATA ROUTID/4HSUPW,4HB /, 54 2 Q31210/4H4.3.,4H1.2-,4H10 /,Q1212A/4H4.3.,4H1.2-,4H12A /, 55 3 Q2118A/4H4.2.,4H2.1-,4H23A /,Q1212B/4H4.3.,4H1.2-,4H12B /, 56 4 Q2118B/4H4.2.,4H2.1-,4H23B /,Q2137A/4H4.3.,4H2.2-,4H37A /, 57 5 Q2137B/4H4.3.,4H2.2-,4H37B / 58 DATA WTYPE/4HSTRA,4HDOUB,4HCRAN,4HCURV/ 59C 60C FIGURE 4.3.1,2-10 KWB 61C 62 DATA TFIG10/0.0,.1,.2,.3,.4,.5,.6,.7,.8,.9,1.0/ 63 DATA DKWB10/1.0,1.08,1.16,1.26,1.36,1.46,1.56,1.67,1.78,1.89,2.0/ 64C 65C FIGURE 4.3.1.2-10 KBW 66C 67 DATA DKBW10/0.0,.13,.29,.45,.62,.80,1.0,1.22,1.45,1.70,2.0/ 68C 69C FIGURE 4.2.2.1-23A (LEFT SIDE) 70C 71 DATA T4218A 72 1 / 0., 0.2, 0.4, 0.6, 0.8, 1.0 , 3*0.0, 73 2 0.0, 0.4, 0.8, 1.2, 1.6, 2.0, 3.0, 4.0, 5.0 / 74 DATA DL218A 75 1 / 0.543, 0.542, 0.541, 0.540, 0.534, 0.526, 76 2 0.400, 0.409, 0.418, 0.430, 0.441, 0.450, 77 3 0.305, 0.328, 0.350, 0.369, 0.387, 0.400, 78 4 0.238, 0.265, 0.295, 0.318, 0.339, 0.356, 79 5 0.198, 0.221, 0.246, 0.274, 0.298, 0.320, 80 6 0.160, 0.185, 0.210, 0.239, 0.262, 0.288, 81 7 0.065, 0.095, 0.122, 0.150, 0.177, 0.210, 82 8 0.000, 0.005, 0.035, 0.062, 0.089, 0.130, 83 9 0.000, 0.000, 0.000, 0.000, 0.002, 0.050 / 84C 85C FIGURE 4.2.2.1-23A (RIGHT SIDE) 86C 87 DATA DR218A 88 1 / 0.445, 0.464, 0.485, 0.500, 0.518, 0.526, 89 2 0.448, 0.455, 0.460, 0.460, 0.459, 0.450, 90 3 0.460, 0.449, 0.438, 0.424, 0.412, 0.400, 91 4 0.450, 0.430, 0.412, 0.394, 0.375, 0.356, 92 5 0.432, 0.410, 0.388, 0.365, 0.343, 0.320, 93 6 0.420, 0.394, 0.369, 0.340, 0.314, 0.288 , 94 7 0.388, 0.354, 0.322, 0.278, 0.244, 0.210, 95 8 0.357, 0.314, 0.273, 0.216, 0.171, 0.130, 96 9 0.325, 0.274, 0.225, 0.154, 0.100, 0.050 / 97C 98C FIGURE 4.2.2.1-23B (LEFT SIDE) 99C 100 DATA T4218B 101 1 / 0., 0.2, 0.4, 0.6, 0.8, 1.0 , 0., 102 2 0.0, 0.5, 1.0, 2.0, 3.0, 4.0, 5.0 / 103 DATA DL218B 104 1 / .665, .665, .665, .665, .665, .665, 105 2 .425, .492, .539, .550, .550, .550, 106C 107 3 .330, .370, .405, .438, .459, .470, 108 4 .184, .215, .250, .284, .318, .350, 109 5 .060, .097, .133, .170, .206, .240, 110 6 .000, .000, .044, .083, .127, .170, 111 7 .000, .000, .000, .020, .063, .105 / 112C 113C FIGURE 4.2.2.1-23B (RIGHT SIDE) 114C 115 DATA DR218B 116 1 / .665, .665, .665, .665, .665, .665, 117 2 .480, .500, .519, .536, .546, .550, 118 3 .338, .388, .430, .458, .471, .470, 119 4 .338, .372, .394, .394, .375, .350, 120 5 .410, .375, .341, .308, .272, .240, 121 6 .377, .338, .294, .251, .211, .170, 122 7 .342, .300, .246, .194, .146, .100 / 123C 124C FIGURE 4.3.1.2-12A (KBW) 125C 126 DATA T4312A/0.0,.1,.2,.3,.4,.5,.6,.7,.8,.9,1.0/ 127 DATA D4312A/0.0,.11,.21,.31,.41,.51,.6,.7,.8,.9,1.0/ 128C 129C FIGURE 4.3.1.2-12B (KWB) 130C 131 DATA T4312B/.015,.1,.2,.3,.4,.6,.8,.975/ 132 DATA D4312B/1.,.975,.956,.947,.941,.950,.978,1.0/ 133C 134C FIGURE 4.3.2.2-37A 135C 136 DATA T4337A/0.0,.4,.8,1.2,1.6,2.,2.4,2.8, 137 1.1,1.0,999999./ 138 DATA D4337A/ 139 1.5,.72,.900,1.08,1.24,1.39,1.53,1.68, 140 2.5,.72,.910,1.09,1.25,1.41,1.57,1.72, 141 3.5,.73,.920,1.11,1.27,1.43,1.59,1.74/ 142C 143C FIGURE 4.3.2.2-37B 144C 145 DATA T4337B/0.0,.1,.2,.3,.4,.5,.6,.8,1.0,2.8, 146 10.2,999999./ 147 DATA D4337B/ 148 10.5,.56,.595,.62,.64,.65,.66,.669,.669,.671, 149 20.5,.54,.578,.60,.62,.638,.649,.66,.669,.671/ 150C 151 NX=NXX+.5 152 DCYL=(DN+D1)/2. 153 MACH=FLC(I+2) 154 BETA=SQRT(MACH**2-1.) 155 RLB=XCOOR(NX) 156 DD=2.0*(SPAN-SPANS) 157 TANLE=TANL 158 IF(TANLE.EQ.0.0)TANLE=.00001 159C 160C ***SUPERSONIC WING-BODY LIFT CURVE SLOPE,BODY IN PRESENCE OF WING*** 161C NON-TRIANGULAR WINGS 162C 163 IF(TAPEXP.EQ.0.0)GO TO 1050 164 ARG1=BETA*ARSTAR*(1.0+TAPEXP) 165 ARG2=1.+TANLE/BETA 166 TRINO=ARG1*ARG2 167 IF(TRINO.LE.4.)GO TO 1030 168 1000 OLE=A(34) 169 DX=RLB-XW-DD/2.*A(38)-CRSTAR 170 IF(DX.LE.(-CRSTAR))RKBW=0. 171 IF(DX.LE.(-CRSTAR))GO TO 1020 172 CALL INTKBW(MACH,OLE,CRSTAR,DD,DX,RKBW,RXAC) 173 1020 KBW=RKBW/(RAD*BETA*(SREF/A(3))*CLAW*(TAPEXP+1.)*(2.*SPAN/DD-1.)) 174 GO TO 1040 175 1030 CONTINUE 176 LGH(1)=11 177 VAR(1)=DD/(2.*SPAN) 178C 179C FIGURE 4.3.1.2-10 KBW 180C 181 CALL INTERX(1,TFIG10,VAR,LGH,DKBW10,KBW,11,11, 182 1 0,0,0,0,0,0,0,0,Q31210,3,ROUTID) 183 1040 CONTINUE 184 GO TO 1060 185C 186C ***SUPERSONIC WING-BODY LIFT CURVE SLOPE,BODY IN PRESENCE OF WING*** 187C TRIANGULAR WING 188C 189 1050 CONTINUE 190 ARG=BETA*ARSTAR 191 IF(ARG.GT.1.)GO TO 1000 192 GO TO 1030 193 1060 CONTINUE 194C 195C ***SUPERSONIC WING-BODY LIFT CURVE SLOPE 196C 197 ALBO=BD(81) 198 IF(BD(81).EQ.UNUSED)ALBO=0.0 199 DO 1070 J=1,NALPHA 200 1070 ALPHAB(J)=FLC(J+22)+ALBO 201 VAR(1)=(SPAN-SPANS)/SPAN 202 LGH(1)=11 203C 204C FIGURE 4.3.1.2-10 KWB 205C 206 CALL INTERX(1,TFIG10,VAR,LGH,DKWB10,KWB,11,11, 207 1 0,0,0,0,0,0,0,0,Q31210,3,ROUTID) 208 CLAWB=CLAW*KWB 209 CLABW=CLAW*KBW 210 CLA=CLABW+CLAWB+CLAB 211C 212C ***SUPERSONIC WING-BODY LIFT AT ANGLE OF ATTACK*** 213C 214 IF(TYPE.NE.WTYPE(1))GO TO 1100 215 IF(ALIW.EQ.0.0.OR.(ALIW.EQ.UNUSED))GO TO 1080 216C 217C FIGURE 4.3.1.2-12A (KBW) INCIDENCE 218C 219 CALL INTERX(1,T4312A,VAR,LGH,D4312A,KKBW,11,11, 220 1 0,0,0,0,0,0,0,0,Q1212A,3,ROUTID) 221C 222C FIGURE 4.3.1.2-12B (KWB) INCIDENCE 223C 224 LGH(1)=8 225 CALL INTERX(1,T4312B,VAR,LGH,D4312B,KKWB,8,8, 226 1 0,0,0,0,0,0,0,0,Q1212B,3,ROUTID) 227 1080 CLI=CLAW*ALIW 228 DETCL=0.0 229 BD(83)=XW+A(161) 230 BD(535)=SPAN-SPANS 231 CALL BODOWG(BD(255),BD(83),BD(535),SPAN,A(27), 232 1 IVBW,GAMMA,NALPHA) 233 ARG1=KWB+KBW 234 ARG2=(KKWB+KKBW)*CLI 235 ARG3=CLAW*(DD/(2.*SPAN)) 236 DO 1090 J=1,NALPHA 237 DETCL=ARG3*ALPHAB(J)*IVBW(J)*GAMMA(J) 238 1090 CL(J)=CLB(J)+ARG1*(CLW(J)-CLI)+ARG2+DETCL 239C 240C ***SUPERSONIC CENTER OF PRESSURE FOR BODY NOSE AND FORBODY*** 241C 242 1100 CONTINUE 243 DELXW=(SPAN-SPANS)*TANLE*COS(ALIW/RAD) 244 RLAP=XW+DELXW-RLN 245 ARG1=RLN 246 IF(RLAP.LT.0.)ARG1=RLN+RLAP 247 IF(RLAP.LT.0.)RLAP=0.0 248 FA=RLAP/DCYL 249 FN=ARG1/DCYL 250 VAR(1)=BETA/FN 251 VAR(2)=FA/FN 252 LGH(1)=6 253 LGH(2)=9 254 IF(BNOSE.EQ.1.)GO TO 1120 255C 256C FIGURE 4.2.2.1-23A LEFT SIDE(XCP) OGIVE 257C 258 IF(VAR(1).GT.1.)GO TO 1110 259 CALL INTERX(2,T4218A,VAR,LGH,DL218A,XCPLN,9,54, 260 1 0,0,0,0,0,0,0,0,Q2118A,3,ROUTID) 261 GO TO 1140 262 1110 VAR(1)=1./VAR(1) 263C 264C FIGURE 4.2.2.1-23A RIGHT SIDE(XCP) OGIVE 265C 266 CALL INTERX(2,T4218A,VAR,LGH,DR218A,XCPLN,9,54, 267 1 0,0,0,0,0,0,0,0,Q2118A,3,ROUTID) 268 GO TO 1140 269 1120 CONTINUE 270C 271C FIGURE 4.2.2.1-23B LEFT SIDE(XCP) CONE 272C 273 LGH(2)=7 274 IF(VAR(1).GT.1.)GO TO 1130 275 CALL INTERX(2,T4218B,VAR,LGH,DL218B,XCPLN,7,42, 276 1 0,0,0,0,0,0,0,0,Q2118B,3,ROUTID) 277 GO TO 1140 278 1130 VAR(1)=1./VAR(1) 279C 280C FIGURE 4.2.2.1-23B RIGHT SIDE(XCP) CONE 281C 282 CALL INTERX(2,T4218B,VAR,LGH,DR218B,XCPLN,7,42, 283 1 0,0,0,0,0,0,0,0,Q2118B,3,ROUTID) 284 1140 CONTINUE 285 XACN=(XCPLN-1.)*(ARG1+RLAP)/CBARR 286C 287C ***SUPERSONIC WING-LIFT CARRYOVER ON BODY*** 288C 289 VAR(1)=BETA*DD/CRSTAR 290 VAR(2)=BETA/TANLE 291 ARG=(XW+CR)/RLB 292 IF(ARG.GT.1.)GO TO 1150 293C 294C FIGURE 4.3.2.2-37A(XAC)B(W) 295C 296 LGH(1)=8 297 LGH(2)=3 298 CALL INTERX(2,T4337A,VAR,LGH,D4337A,XACA,8,24, 299 1 0,0,0,0,1,0,0,0,Q2137A,3,ROUTID) 300 GO TO 1160 301C 302C FIGURE 4.3.2.2-37B(XAC)B(W) 303C 304 1150 LGH(1)=10 305 LGH(2)=2 306 CALL INTERX(2,T4337B,VAR,LGH,D4337B,XACA,10,20, 307 1 0,0,0,0,0,0,0,0,Q2137B,3,ROUTID) 308 1160 XACBW=XACA*CRSTAR/CBARR 309 XACW=XACW*CRSTAR/CBARR 310C 311C ***SUPERSONIC WING-BODY PITCHING MOMENT SLOPE*** 312C 313 DNUM=XACN*CLAB+XACW*CLAWB+XACBW*CLABW 314 DNOM=CLAB+CLAWB+CLABW 315 XAC =DNUM/DNOM 316 CMA=(DXCG/CBARR-XAC)*CLA 317C 318C ***SUPERSONIC WING-BODY DRAG*** 319C 320 CDOWB=CDOW+CDOB 321 DO 1170 J=1,NALPHA 322 COSA=COS(FLC(J+22)/RAD) 323 SINA=SIN(FLC(J+22)/RAD) 324 CD(J)=CDOW+CDL(J)+CDB(J) 325 CN(J)=CL(J)*COSA+CD(J)*SINA 326C 327C COMPUTE DELTA XCP WING-BODY 328C 329 DXCPWB=A(173)/CBARR-SLG(134) 330C 331C COMPUTE DELTA XCP BODY-WING 332C 333 DXCPBW=A(173)/CBARR-SWB(8) 334C 335C COMPUTE DELTA CN VORTEX 336C 337 DCNV=SWB(11+J)*SWB(39+J)*SWB(5)/(2*SPAN)*BD(254+J)*WING(101) 338 1 /RAD 339C 340C COMPUTE WING-BODY PITCHING MOMENT 341C 342 BW(40+J)=BODY(40+J)+WING(60+J)*SWB(35)*DXCPWB 343 1 +WING(101)*SYNA(4)*SWB(2)*DXCPWB/RAD 344 2 +WING(60+J)*SWB(11)*DXCPBW 345 3 +WING(101)*SYNA(4)*SWB(37)*DXCPBW/RAD 346 4 +DCNV*DXCPWB 347 5 +WING(80+J)*(SYNA(3)-SYNA(5))/CBARR 348 1170 CA(J)=CD(J)*COSA-CL(J)*SINA 349 RETURN 350 END 351