1 SUBROUTINE WBLIFT(A,B,DB,AIW,WB,BW,FACT,BODY,WING,WINGIN) 2C 3 COMMON /OVERLY/ NLOG,NMACH,I,NALPHA,IG 4 COMMON /CONSNT/ PI, DEG, UNUSED, RAD 5 COMMON /FLGTCD/ FLC(160) 6 DIMENSION ROUTID(2),Q1210A(3),Q1210B(3),Q212A1(4),Q212A2(4), 7 1 Q1212C(3),Q412B(3),Q412C(3) 8 DIMENSION A(195),B(49),WB(39),BODY(101),WING(101),WINGIN(4) 9 DIMENSION FACT(1),BW(1),ANG(20),CB(6),QCLINT(2) 10 DIMENSION X10A(11),Y10A(11),C10A(6) 11 DIMENSION X10B(11),Y10B(11),C10B(6) 12 DIMENSION X12A1(11),Y12A1(11),C12A1(6) 13 DIMENSION X12A2(11),Y12A2(11),C12A2(6) 14 DIMENSION X12C(13),Y12C(13),C12C(6) 15 DIMENSION XA12(5),XB12(7),Y412C(35),Y412B(35) 16 DATA ROUTID /4HWBLI,4HFT / 17 DATA Q1210A /4H4.3.,4H1.2-,4H10-A/, 18 1 Q1210B /4H4.3.,4H1.2-,4H10-B/, 19 2 Q212A1 /4H4.3.,4H1.2-,4H12-A,4H1 /, 20 3 Q212A2 /4H4.3.,4H1.2-,4H12-A,4H2 /, 21 4 Q1212C /4H4.3.,4H1.2-,4H12-C/, 22 5 Q412B /4H4.3., 4H1.4-, 4H12B /, 23 6 Q412C /4H4.3., 4H1.4-, 4H12C / 24C 25C********* KW(B) VS D/B DATA FIGURE 4.3.1.2-10-A 26C 27 DATA X10A/0.0,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,1.0/ 28 DATA Y10A/1.0,1.08,1.16,1.26,1.36,1.46,1.56,1.67,1.78,1.89,2.0/ 29 DATA I10A/0/ 30C 31C **** KB(W) VS D/B DATA FIGURE 4.3.1.2-10-B 32C 33 DATA X10B/0.0,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,1.0/ 34 DATA Y10B/0.0,0.13,0.29,0.45,0.62,0.80,1.0,1.22,1.45,1.70,2.0/ 35 DATA I10B/0/ 36C 37C *** FIGURE 4.3.1.2-12-A1 38C 39 DATA X12A1/0.0,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,1.0/ 40 DATA Y12A1/1.0,0.97,0.95,4*0.94,0.95,0.96,0.98,0.99/ 41 DATA I12A1/0/ 42C 43C********* FIGURE 4.3.1.2-12-A2 ********************** 44C 45 DATA X12A2/0.0,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,1.0/ 46 DATA Y12A2/0.0,0.11,0.21,0.31,0.41,0.51,0.60,0.70,0.80,0.90,1.0/ 47 DATA I12A2/0/ 48C 49C********* FIGURE 4.3.1.2-12-C ********************** 50C 51 DATA X12C/0.0,0.1,0.15,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.83,0.9,1.0/ 52 DATA Y12C/2*1.0,0.999,0.99,0.98,0.965,0.95,0.933,2*0.92,0.928, 53 10.95,1.0/ 54 DATA I12C/0/ 55C 56C********* FIGURE 4.3.1.4-12 ********************** 57C 58 DATA XA12 /1., 2., 4., 6., 12. / 59 DATA XB12 / 0., 0.05, 0.10, 0.15, 0.20, 0.25, 0.30 / 60 DATA Y412B / 61 1 1.0, 0.998, 0.995, 0.989, 0.982, 0.968, 0.950, 62 2 1.0, 0.995, 0.989, 0.978, 0.963, 0.937, 0.917, 63 3 1.0, 0.992, 0.982, 0.965, 0.942, 0.900, 0.864, 64 4 1.0, 0.967, 0.932, 0.911, 0.907, 0.945, 1.038, 65 5 1.0, 0.983, 0.968, 0.962, 0.977, 1.027, 1.134 / 66 DATA Y412C / 67 1 1.0, 1.013, 1.017, 1.013, 1.000, 0.982, 0.956, 68 2 1.0, 1.003, 1.001, 0.992, 0.973, 0.937, 0.894, 69 3 1.0, 0.989, 0.973, 0.944, 0.898, 0.822, 0.745, 70 4 1.0, 0.980, 0.943, 0.879, 0.758, 0.648, 0.613, 71 5 1.0, 0.942, 0.845, 0.688, 0.594, 0.552, 0.532 / 72 DATA IY / 0 /, QCLINT / 4HCLIN, 4HT / 73C 74C COMPUTE BODY-DIAMETER-TO-WING-SPAN RATIO 75C 76 SSPN=WINGIN(4) 77 RATIO= DB/(2.0*SSPN) 78 AAA=1.0 79 DO 1000 J=1,NALPHA 80 ANG(J) = FLC(J+22)+AIW-B(49) 81 1000 CONTINUE 82 DO 1040 J=1,NALPHA 83 IF(RATIO.GT.0.80) GO TO 1020 84C 85C********* FIGURE 4.3.1.2-10-A 86C 87 CALL TBFUNX(RATIO,WB(2),DYDX,11,X10A,Y10A,C10A,I10A,MI,NG, 88 1 0,0,Q1210A,3,ROUTID) 89C 90C********* FIGURE 4.3.1.2-10-B 91C 92 CALL TBFUNX(RATIO,WB(3),DYDX,11,X10B,Y10B,C10B,I10B,MI,NG, 93 1 0,0,Q1210B,3,ROUTID) 94 WB(4)= WB(2)*WING(101)*AAA 95 WB(5)= WB(3)*WING(101)*AAA 96 BW(101)= BODY(101)+WB(4)+WB(5) 97 IF(AIW.NE.0.0) GO TO 1010 98 GO TO 1030 99C 100C********* FIGURE 4.3.1.2-12-A1 101C 102 1010 CALL TBFUNX(RATIO,WB(7),DYDX,11,X12A1,Y12A1,C12A1,I12A1,MI,NG, 103 1 0,0,Q212A1,4,ROUTID) 104C 105C********* FIGURE 4.3.1.2-12-A2 106C 107 CALL TBFUNX(RATIO,WB(8),DYDX,11,X12A2,Y12A2,C12A2,I12A2,MI,NG, 108 1 0,0,Q212A2,4,ROUTID) 109 WB(9)=WB(7)*WING(101)*AAA 110 WB(10)=WB(8)*WING(101)*AAA 111 WB(11)=WB(9)+WB(10) 112 GO TO 1030 113C 114C**** CALCULATIONS WITH WING EXTENDING ENTIRE LENGTH OF BODY ******* 115C**** (FOR LARGE BODY-DIAMETER-TO-WING-SPAN RATIOS) ******* 116C**** ******* 117C********* FIGURE 4.3.1.2-12-C 118C 119 1020 CALL TBFUNX(RATIO,WB12,DYDX,13,X12C,Y12C,C12C,I12C,MI,NG, 120 1 0,0,Q1212C,3,ROUTID) 121 BW(101)= WB12*WING(101)*AAA 122C 123C********* WING BODY LIFT IN NON-LINEAR ************ 124C********* ANGLE-OF-ATTACK RANGE ************ 125C 126 1030 CONTINUE 127C 128C*********** LIFT COEFFICIENT (CL) CALCULATION ************************* 129C 130 ALPEF=FLC(J+22)-B(49)+((WB(7)+WB(8))/(WB(2)+WB(3)))*AIW 131 CALL TBFUNX(ALPEF,CLINT,DYDX,NALPHA,ANG,WING(21), 132 1 CB,IY,MI,NG,1,1,QCLINT,2,ROUTID) 133 BW(J+20)=BODY(J+20)+(WB(2)+WB(3))*CLINT 134 BW(J+20)=BW(J+20)+FACT(J+1)*FACT(J+21)*B(J+22)*FACT(1)* 135 1 WING(101) 136C 137C*********** NORMAL FORCE (CN) CALCULATION ***************************** 138C 139 BW(J+60)=BW(J+20)*COS(B(J+22)/RAD)+BW(J)*SIN(B(J+22)/RAD) 140C 141C ******* SEE SUBROUTINE WBCM FOR CA CALCULATION ******* 142C 143 1040 CONTINUE 144 IF(RATIO .GT. 0.30) GO TO 1050 145 CALL TLINEX(XA12,XB12,Y412B,5,7,A(160),RATIO,WB(20), 146 1 0,0,0,0,Q412B,3,ROUTID) 147 CALL TLINEX(XA12,XB12,Y412C,5,7,A(160),RATIO,WB(21), 148 1 0,0,0,0,Q412C,3,ROUTID) 149 WB(22) = WB(20)*B(44) 150 WB(23) = WB(21)*B(43) 151 1050 CONTINUE 152 RETURN 153 END 154