1 SUBROUTINE AIRFOL 2C 3C CALCULATE NACA DESIGNATED AIRFOIL COORDINATES 4C 5 COMMON /IBODY/ PB,NACA(80) 6 COMMON /IWING/ PW, X(60) 7 COMMON / IHT / PHT, XU(60),XL(60) 8 COMMON / IVT / PVT, YUN(60),YLN(60) 9 COMMON / IBW / PBW,L,I,J,K,II,JJ,KK,III,JJJ,KKK,LLL 10 COMMON / IBH / PBH, THN(60),CAM(60) 11 COMMON /IBWHV/ PBWHV, RHO,TMAX 12 COMMON /FLOLOG/ DUM(29),PART 13 LOGICAL DUM,PART 14 INTEGER A4HW,A4HH,A4HV,A4HF 15 DIMENSION THN2(60) 16 DATA A4HW,A4HH,A4HV,A4HF/4HW ,4HH ,4HV ,4HF / 17C 18C DECODE THE USERS INPUT NACA DESIGNATION 19C 20 CALL DECODE(NACA,NA) 21C 22C CALCULATE THE AIRFOIL COORDINATES 23C 24 IF(PART)WRITE(6,1100) 25 IF(PART .AND. NACA(6).EQ.A4HW)WRITE(6,1230) 26 IF(PART .AND. NACA(6).EQ.A4HH)WRITE(6,1240) 27 IF(PART .AND. NACA(6).EQ.A4HV)WRITE(6,1250) 28 IF(PART .AND. NACA(6).EQ.A4HF)WRITE(6,1260) 29C 30 GO TO (1000,1010,1020,1030,1040,1050,1060), NA 31C 32 1000 IF(PART)WRITE(6,1110)I,J,K,II 33C 34C** CALCULATE NACA 4-DIGIT AIRFOIL COORDINATES 35C 36 CALL COORD4 37 GO TO 1080 38 1010 IF(PART)WRITE(6,1120)I,J,K,II,KK,III 39C 40C** CALCULATE NACA MODIFIED 4-DIGIT AIRFOIL COORDINATES 41C 42 CALL CORD4M 43 GO TO 1080 44 1020 IF(PART)WRITE(6,1130)I,J,K,II,JJ 45C 46C** CALCULATE NACA 5-DIGIT AIRFOIL COORDINATES 47C 48 CALL COORD5 49 GO TO 1080 50 1030 IF(PART)WRITE(6,1140)I,J,K,II,JJ,III,JJJ 51C 52C** CALCULATE NACA MODIFIED 5-DIGIT AIRFOIL COORDINATES 53C 54 CALL CORD5M 55 GO TO 1080 56 1040 IF(PART)WRITE(6,1150)I,J,II,JJ,KK 57C 58C** CALCULATE NACA 1-SERIES AIRFOIL COORDINATES 59C 60 CALL COORD1 61 GO TO 1080 62 1050 IF(PART .AND. (K .EQ. 0 .AND. II .EQ. 0)) 63 1 WRITE(6,1160)I,J,JJ,KK,III 64 IF(PART .AND. (K .NE. 0 .AND. II .EQ. 0)) 65 1 WRITE(6,1170)I,J,K,JJ,KK,III 66 IF(PART .AND. (K .EQ. 0 .AND. II .NE. 0)) 67 1 WRITE(6,1180)I,J,JJ,KK,III 68 IF(PART .AND. (K .NE. 0 .AND. II .NE. 0)) 69 1 WRITE(6,1190)I,J,K,JJ,KK,III 70 IF(PART .AND. (JJJ .GE. 1)) WRITE(6,1200)JJJ 71C 72C** CALCULATE NACA 6-SERIES AIRFOIL COORDINATES 73C 74 CALL COORD6 75 GO TO 1080 76 1060 IF(I.NE.2)GO TO 1070 77 J=5 78 K=0 79 II=0 80 1070 IF(PART)WRITE(6,1270)I,J,K,II,JJ,KK,III,JJJ,KKK,LLL 81C 82C** CALCULATE GEOMTRY FOR SUPERSONIC AIRFOILS 83C 84 CALL CORDSP 85C 86C** CALCULATE AIRFIOL SECTION X Y COORDINATES OR THICKNESS/CAMBER 87C DISTRIBUTION 88C 89 CALL XYCORD(0,0) 90 1080 IF(PART)WRITE(6,1210) 91C 92 DO 1090 M=1,L 93 THN2(M)=2.*THN(M) 94 1090 CONTINUE 95 IF(PART)WRITE(6,1220)(XU(M),YUN(M),XL(M),YLN(M),X(M),CAM(M), 96 1 THN2(M),M=1,L) 97 RETURN 98C 99 1100 FORMAT(1H1,29X,75HAUTOMATED STABILITY AND CONTROL METHODS PER APRI 100 1L 1976 VERSION OF DATCOM ) 101 1110 FORMAT(1H ,62X,6H NACA ,4I1) 102 1120 FORMAT(1H ,60X,6H NACA ,4I1,3H - ,2I1) 103 1130 FORMAT(1H ,62X,6H NACA ,5I1) 104 1140 FORMAT(1H ,60X,6H NACA ,5I1,3H - ,2I1) 105 1150 FORMAT(1H ,61X,6H NACA ,2I1,3H - ,3I1) 106 1160 FORMAT(1H ,62X,6H NACA ,2I1,1H-,3I1) 107 1170 FORMAT(1H ,60X,6H NACA ,2I1,1H,,I1,1H-,3I1) 108 1180 FORMAT(1H ,61X,6H NACA ,2I1,1HA,3I1) 109 1190 FORMAT(1H ,60X,6H NACA ,2I1,1H,,I1,1HA,3I1) 110 1200 FORMAT(1H ,65X,4HA=0.,I1) 111 1210 FORMAT(1H ,3X,15H UPPER ABSCISSA,4X,15H UPPER ORDINATE,4X, 112 1 15H LOWER ABSCISSA,4X,15H LOWER ORDINATE,6X, 113 2 16HX-FRACTION CHORD,4X,9HMEAN LINE,4X,9HTHICKNESS) 114 1220 FORMAT(8X,F8.5,11X,F8.5,10X,F8.5,10X,F8.5,13X,F8.5,10X, 115 1 F8.5,6X,F8.5) 116 1230 FORMAT(1H ,55X,23HWING SECTION DEFINITION) 117 1240 FORMAT(1H ,50X,34HHORIZONTAL TAIL SECTION DEFINITION) 118 1250 FORMAT(1H ,51X,32HVERTICAL TAIL SECTION DEFINITION) 119 1260 FORMAT(1H ,52X,30HVENTRAL FIN SECTION DEFINITION ) 120 1270 FORMAT(1H ,54X,8H NACA S-,I1,1H-,2I1,1H.,I1,1H-,2I1,1H.,I1, 121 1 1H-,2I1,1H.,I1) 122 END 123