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