1 SUBROUTINE WBDRAG (A,B,D,BD,WB,BW,BODY,WING,KBODY,KWING) 2C 3C *** CALCULATE SUBSONIC WING-BODY DRAG COEFFICIENT 4C 5 COMMON /CONSNT/ PI,DEG,UNUSED,RAD,KAND 6 COMMON /OVERLY/ NLOG,NMACH,I,NALPHA,IG,NF,LF,K 7 DIMENSION ROUTID(2),Q33137(3) 8 9C AJT DIMENSION A(195),B(49),BD(50),WB(39),D(55),BW(21),BODY(2),WING(2) 10C AJT1BODY(380),WING(380) 11 DIMENSION A(1),B(1),BD(1),WB(1),D(1),BW(1), 12 1BODY(1),WING(1) 13 LOGICAL KBODY,KWING 14C 15C********* WING-BODY DRAG CALCULATIONS ******* 16C *** FIGURE 4.3.3.1-37 17C X237= R(L)FUS X137= MACH NO. Y37= R(WB) 18C 19 DIMENSION X237(19),X137(7),Y37(133) 20 DATA X237/3.E06,5.E06,7.E06,1.E07,1.5E07,2.E07,2.5E07,3.E07, 21 13.5E07,4.E07,4.5E07,5.E07,6.E07,7.E07,8.E07,1.E08,1.5E08,2.E08, 22 27.E08/ 23 DATA X137/0.25,0.40,0.60,0.70,0.80,0.85,0.90/ 24 DATA Y37/1.063,1.070,1.073,1.076,1.072,1.066,1.057,1.045,1.025, 25 1.9935,.9650,.9515,.9390,.9335,.9310,.9280,.9230,.9225,.9540 , 26 21.020,1.023,1.028,1.036,1.050,2*1.058,1.050,1.032,1.018,1.008, 27 31.001,.9920,.9875,.9845,.9800,.9770,.9755,.9750 , .9800,.9840, 28 4.9890,.9965,1.0080,1.0200,1.0325,1.0375,1.0350,1.0315,1.0280, 29 51.0230,1.0190,1.0155,5*1.0150 , .9550,.9600,.9647,.9725,.9830, 30 6.9950,1.0085,1.0130,1.0140,1.0145,9*1.0150 , .9250,.9300,.9340, 31 7.9420,.9530,.9655,.9775,.9885,.9965,1.0025,1.0080,1.0110,1.0145, 32 86*1.0150 , .9025,.9070,.9120,.9190,.9310,.9425,.9540,.9690,.9820, 33 9.9920,.9985,1.0035,1.0110,1.0140,5*1.015 , .8700,.8715,.8775, 34 A.8840,.8960,.9090,.9225,.9400,.9570,.9725,.9865,.9935,1.0065, 35 B1.0120,5*1.0150/ 36 DATA Q33137/4H4.3.,4H3.1-,4H37 /,ROUTID/4HWBDR,4HAG / 37C 38C********* WING-BODY ZERO LIFT DRAG ***************** 39C 40 WB(19)= A(129)*BD(1) 41 CALL TLINEX(X137,X237,Y37,7,19,B(1),WB(19),WB(18), 42 1 2,2,2,1,Q33137,3,ROUTID) 43 WB(17)= (D(20)+BD(59))*WB(18)+BD(60) 44 WB(6)=WB(17) 45C 46C********* WING-BODY DRAG AT ANGLE-OF-ATTACK ************ 47C 48 DO 1000 J=1,NALPHA 49 BW(J)= WB(17)+BD(J+214)+D(J+35) 50 IF((KBODY .OR. KWING) .AND. (BODY(J) .NE. UNUSED .AND. 51 1 WING(J) .NE. UNUSED)) BW(J) = BODY(J)+WING(J) 52 1000 CONTINUE 53 RETURN 54 END 55