* Gfortran issue
@ 2014-07-29 7:31 Jerome Huck
0 siblings, 0 replies; 2+ messages in thread
From: Jerome Huck @ 2014-07-29 7:31 UTC (permalink / raw)
To: gcc-help, gcc
[-- Attachment #1: Type: text/plain, Size: 571 bytes --]
from Jerome Huck
Good morning.
I did use Gfortran GCC 9.0 on Windows 7 64 bits on an old Fortran77. I
attached both the source code and the GCC outputs.
I have warning with COMMON. The COMMONS are the same along the code...
When compiled I have warnings with different sizes !!!
I do not know if it is a bug. I will say it is an issue.
There were some bugs/issues in the past see :
https://gcc.gnu.org/bugzilla/show_bug.cgi?id=45044
https://gcc.gnu.org/bugzilla/show_bug.cgi?id=45045
If you can give me some clues/hints on the subject.
Best regards.
Jerome Huck.
[-- Attachment #2: vlm.f --]
[-- Type: text/plain, Size: 20601 bytes --]
C PROGRAM No. 12: RECTANGULAR LIFTING SURFACE (VLM)
C -------------------------------------------------
C 3D-VLM CODE FOR SIMPLE WING PLANFORMS WITH GROUND EFFECT (BY JOE KATZ, 1974).
DIMENSION QF(6,14,3),QC(4,13,3),DS(4,13,4)
DIMENSION GAMA(4,13),DL(4,13),DD(4,13),DP(4,13)
DIMENSION A(52,52),GAMA1(52),DW(52),IP(52)
DIMENSION A1(5,13),DLY(13),GAMA1J(5),X(4)
COMMON/NO1/ DS,X,B,C,S,AR,SN1,CS1
COMMON/NO2/ IB,JB,CH,SIGN
COMMON/NO3/ A1
COMMON/NO4/ QF,QC,DXW
C
C ==========
C INPUT DATA
C ==========
C
IB=4
JB=13
X(1)=0.
X(2)=0.
X(3)=4.
X(4)=4.
B=13.
VT=1.0
ALPHA1=5.0
1000 continue
print*,' '
WRITE(6,101)
print*,' '
print*,' Input the x coordinates of the wing''s 4 corner points.'
print*,' '
print*,'X(1) is the root L.E., X(2) is the tip L.E., '
print*,'X(3) is the tip T.E., and X(4) is the root T.E.'
print*,' '
print*,' 2------3 '
print*,' | | '
print*,' | | '
print*,' | | '
print*,' | | '
print*,' 1------4 '
print*,' '
read*,x(1),x(2),x(3),x(4)
print*, ' Input the Wing Semi-Span, B (0 to stop)'
read*,b
print*,' Input alpha in degrees.'
read*,alpha1
if(b.eq.0.)stop
CH=1000.
C X(1) TO X(4) ARE X-COORDINATES OF THE WING'S FOUR CORNERPOINTS.
C B - WING SPAN, VT - FREE STREAM SPEED, B - WING SPAN,
C CH - HEIGHT ABOVE GROUND
C
C CONSTANTS
DXW=100.0*B
DO 1 I=1,IB
DO 1 J=1,JB
C GAMA(I,J)=1.0 IS REQUIRED FOR INFLUENCE MATRIX CALCULATIONS.
1 GAMA(I,J)=1.0
RO=1.
PAY=3.141592654
ALPHA=ALPHA1*PAY/180.
SN1=SIN(ALPHA)
CS1=COS(ALPHA)
IB1=IB+1
IB2=IB+2
JB1=JB+1
C
C =============
C WING GEOMETRY
C =============
C
CALL GRID
WRITE(6,101)
WRITE(6,102) ALPHA1,B,C,S,AR,VT,IB,JB,CH
C
C ========================
C AERODYNAMIC CALCULATIONS
C ========================
C
C INFLUENCE COEFFICIENTS CALCULATION
C
K=0
DO 14 I=1,IB
DO 14 J=1,JB
SIGN=0.0
K=K+1
CALL WING(QC(I,J,1),QC(I,J,2),QC(I,J,3),GAMA,U,V,W,1.0,I,J)
L=0
DO 10 I1=1,IB
DO 10 J1=1,JB
L=L+1
C A(K,L) - IS THE NORMAL VELOCITY COMPONENT DUE TO A UNIT VORTEX
C LATTICE.
10 A(K,L)=A1(I1,J1)
C ADD INFLUENCE OF WING'S OTHER HALF
CALL WING(QC(I,J,1),-QC(I,J,2),QC(I,J,3),GAMA,U,V,W,1.0,I,J)
L=0
DO 11 I1=1,IB
DO 11 J1=1,JB
L=L+1
11 A(K,L)=A(K,L)+A1(I1,J1)
IF(CH.GT.100.0) GOTO 12
C ADD INFLUENCE OF MIRROR IMAGE (DUE TO GROUND)
SIGN=10.0
CALL WING(QC(I,J,1),QC(I,J,2),-QC(I,J,3),GAMA,U,V,W,1.0,I,J)
L=0
DO 8 I1=1,IB
DO 8 J1=1,JB
L=L+1
8 A(K,L)=A(K,L)+A1(I1,J1)
C ADD MIRROR IMAGE INFLUENCE OF WING'S OTHER HALF.
CALL WING(QC(I,J,1),-QC(I,J,2),-QC(I,J,3),GAMA,U,V,W,1.0,I,J)
L=0
DO 9 I1=1,IB
DO 9 J1=1,JB
L=L+1
9 A(K,L)=A(K,L)+A1(I1,J1)
SIGN=0.0
12 CONTINUE
C
13 CONTINUE
C
C CALCULATE WING GEOMETRICAL DOWNWASH
C
UINF=VT
VINF=0.0
WINF=0.0
C THIS IS THE GENERAL FORMULATION FOR RIGHT HAND SIDE.
DW(K)=-(UINF*DS(I,J,1)+VINF*DS(I,J,2)+WINF*DS(I,J,3))
14 CONTINUE
C
C SOLUTION OF THE PROBLEM: DW(I)=A(I,J)*GAMA(I)
C
K1=IB*JB
DO 15 K=1,K1
15 GAMA1(K)=DW(K)
CALL DECOMP(K1,52,A,IP)
16 CONTINUE
CALL SOLVER(K1,52,A,GAMA1,IP)
C HERE * THE SAME ARRAY SIZE IS REQUIRED,
C AS SPECIFIED IN THE BEGINNING OF THE CODE
C
C WING VORTEX LATTICE LISTING
C
K=0
DO 17 I=1,IB
DO 17 J=1,JB
K=K+1
17 GAMA(I,J)=GAMA1(K)
C
C ==================
C FORCES CALCULATION
C ==================
C
FL=0.
FD=0.
FM=0.
QUE=0.5*RO*VT*VT
DO 20 J=1,JB
DLY(J)=0.
DO 20 I=1,IB
IF(I.EQ.1) GAMAIJ=GAMA(I,J)
IF(I.GT.1) GAMAIJ=GAMA(I,J)-GAMA(I-1,J)
DYM=QF(I,J+1,2)-QF(I,J,2)
DL(I,J)=RO*VT*GAMAIJ*DYM
C INDUCED DRAG CALCULATION
CALL WING(QC(I,J,1),QC(I,J,2),QC(I,J,3),GAMA,U1,V1,W1,0.0,I,J)
CALL WING(QC(I,J,1),-QC(I,J,2),QC(I,J,3),GAMA,U2,V2,W2,0.0,I,J)
IF(CH.GT.100.0) GOTO 194
CALL WING(QC(I,J,1),QC(I,J,2),-QC(I,J,3),GAMA,U3,V3,W3,0.0,I,J)
CALL WING(QC(I,J,1),-QC(I,J,2),-QC(I,J,3),GAMA,U4,V4,W4,0.0,I,J)
GOTO 195
194 W3=0.
W4=0.
195 WIND=W1+W2-W3-W4
C ADD INFLUENCE OF MIRROR IMAGE (GROUND).
ALFI=-WIND/VT
DD(I,J)=RO*DYM*VT*GAMAIJ*ALFI
C
DP(I,J)=DL(I,J)/DS(I,J,4)/QUE
DLY(J)=DLY(J)+DL(I,J)
FL=FL+DL(I,J)
FD=FD+DD(I,J)
FM=FM+DL(I,J)*(QF(I,J,1)-X(1))
20 CONTINUE
CL=FL/(QUE*S)
CD=FD/(QUE*S)
CM=FM/(QUE*S*C)
C
C OUTPUT
C
WRITE(6,104) CL,FL,CM,CD
WRITE(6,110)
DO 21 J=1,JB
DO 211 I=2,IB
211 GAMA1J(I)=GAMA(I,J)-GAMA(I-1,J)
DLYJ=DLY(J)/B*JB
21 WRITE(6,103) J,DLYJ,DP(1,J),DP(2,J),DP(3,J),DP(4,J),GAMA(1,J),
1GAMA1J(2),GAMA1J(3),GAMA1J(4)
C
C END OF PROGRAM
100 CONTINUE
C
C FORMATS
C
101 FORMAT(1H ,/,20X,'WING LIFT DISTRIBUTION CALCULATION (WITH GROUND
1 EFFECT)',/,20X,56('_'))
102 FORMAT(1H ,/,10X,'ALFA:',F10.2,8X,'B :',
1F10.2,8X,'C : ',F13.2,/,10X,
2'S :',F10.2,8X,'AR :',F10.2,8X,'V(INF) :',F10.2,/,10X,
3'IB :',I10,8X,'JB :',I10,8X,'L.E. HEIGHT:', F8.2,/)
103 FORMAT(1H ,I3,' I ',F9.3,' II ',4(F9.3,' I '),' I ',4(F9.3,' I '))
104 FORMAT(/,1H ,'CL=',F10.4,2X,'L=',F10.4,4X,'CM=',F10.4,3X,
1'CD=',F13.7)
110 FORMAT(1H ,/,5X,'I DL',4X,'II',22X,'DCP',22X,'I I',25X,
1'GAMA',/,118('='),/,5X,'I',15X,'I= 1',11X,'2',11X,'3',11X,
2'4',5X,'I I',5X,'1',11X,'2',11X,'3',11X,'4',/,118('='))
112 FORMAT(1H ,'QF(I=',I2,',J,X.Y.Z)= ',15(F6.1))
113 FORMAT(1H ,110('='))
C
GOTO 1000
END
C
SUBROUTINE GRID
DIMENSION QF(6,14,3),QC(4,13,3),DS(4,13,4),X(4)
COMMON/NO1/ DS,X,B,C,S,AR,SN1,CS1
COMMON/NO2/ IB,JB,CH,SIGN
COMMON/NO4/ QF,QC,DXW
C
PAY=3.141592654
C X(1) - IS ROOT L.E., X(2) TIP L.E., X(3) TIP T.E., AND X(4) IS ROOT T.E.
C IB: NO. OF CHORDWISE BOXES, JB: NO. OF SPANWISE BOXES
IB1=IB+1
IB2=IB+2
JB1=JB+1
C
C WING FIXED VORTICES LOCATION ( QF(I,J,(X,Y,Z))...)
C
DY=B/JB
DO 3 J=1,JB1
YLE=DY*(J-1)
XLE=X(1)+(X(2)-X(1))*YLE/B
XTE=X(4)+(X(3)-X(4))*YLE/B
C XLE AND XTE ARE L.E. AND T.E. X-COORDINATES
DX=(XTE-XLE)/IB
DO 1 I=1,IB1
QF(I,J,1)=(XLE+DX*(I-0.75))*CS1
QF(I,J,2)=YLE
C Note this vvv is different from the original Katz version
QF(I,J,3)=-QF(I,J,1)*SN1+CH
1 CONTINUE
C WAKE FAR FIELD POINTS
QF(IB2,J,1)=XTE+DXW
QF(IB2,J,2)=QF(IB1,J,2)
3 QF(IB2,J,3)=QF(IB1,J,3)
C
C WING COLOCATION POINTS
C
DO 4 J=1,JB
DO 4 I=1,IB
QC(I,J,1)=(QF(I,J,1)+QF(I,J+1,1)+QF(I+1,J+1,1)+QF(I+1,J,1))/4
QC(I,J,2)=(QF(I,J,2)+QF(I,J+1,2)+QF(I+1,J+1,2)+QF(I+1,J,2))/4
QC(I,J,3)=(QF(I,J,3)+QF(I,J+1,3)+QF(I+1,J+1,3)+QF(I+1,J,3))/4
C
C COMPUTATION OF NORMAL VECTORS
C
CALL PANEL(QF(I,J,1),QF(I,J,2),QF(I,J,3),QF(I+1,J,1),QF(I+1,J,2),
1QF(I+1,J,3),QF(I,J+1,1),QF(I,J+1,2),QF(I,J+1,3),QF(I+1,J+1,1),
2QF(I+1,J+1,2),QF(I+1,J+1,3),DS(I,J,1),DS(I,J,2),DS(I,J,3),
3DS(I,J,4))
4 CONTINUE
C
C B -IS SEMI SPAN, C -AV. CHORD, S - AREA
S=0.5*(X(3)-X(2)+X(4)-X(1))*B
C=S/B
AR=2.*B*B/S
C
RETURN
END
C
SUBROUTINE PANEL(X1,Y1,Z1,X2,Y2,Z2,X3,Y3,Z3,X4,Y4,Z4,C1,C2,C3,S)
C CALCULATION OF PANEL AREA AND NORMAL VECTOR.
A1=X2-X3
A2=Y2-Y3
A3=Z2-Z3
B1=X4-X1
B2=Y4-Y1
B3=Z4-Z1
C NORMAL VECTOR
X=A2*B3-A3*B2
Y=B1*A3-A1*B3
Z=A1*B2-A2*B1
A=SQRT(X**2+Y**2+Z**2)
C1=X/A
C2=Y/A
C3=Z/A
C CALCULATION OF PANEL AREA
E1=X3-X1
E2=Y3-Y1
E3=Z3-Z1
F1=X2-X1
F2=Y2-Y1
F3=Z2-Z1
C NORMAL AREAS (F*B+B*E)
S11=F2*B3-F3*B2
S12=B1*F3-F1*B3
S13=F1*B2-F2*B1
S21=B2*E3-B3*E2
S22=E1*B3-B1*E3
S23=B1*E2-B2*E1
S=0.5*(SQRT(S11**2+S12**2+S13**2)+SQRT(S21**2+S22**2+S23**2))
RETURN
END
C
SUBROUTINE VORTEX(X,Y,Z,X1,Y1,Z1,X2,Y2,Z2,GAMA,U,V,W)
C SUBROUTINE VORTEX CALCULATES THE INDUCED VELOCITY (U,V,W) AT A POI
C (X,Y,Z) DUE TO A VORTEX ELEMENT VITH STRENGTH GAMA PER UNIT LENGTH
C POINTING TO THE DIRECTION (X2,Y2,Z2)-(X1,Y1,Z1).
PAY=3.141592654
RCUT=1.0E-10
C CALCULATION OF R1 X R2
R1R2X=(Y-Y1)*(Z-Z2)-(Z-Z1)*(Y-Y2)
R1R2Y=-((X-X1)*(Z-Z2)-(Z-Z1)*(X-X2))
R1R2Z=(X-X1)*(Y-Y2)-(Y-Y1)*(X-X2)
C CALCULATION OF (R1 X R2 )**2
SQUARE=R1R2X*R1R2X+R1R2Y*R1R2Y+R1R2Z*R1R2Z
C CALCULATION OF R0(R1/R(R1)-R2/R(R2))
R1=SQRT((X-X1)*(X-X1)+(Y-Y1)*(Y-Y1)+(Z-Z1)*(Z-Z1))
R2=SQRT((X-X2)*(X-X2)+(Y-Y2)*(Y-Y2)+(Z-Z2)*(Z-Z2))
IF((R1.LT.RCUT).OR.(R2.LT.RCUT).OR.(SQUARE.LT.RCUT)) GOTO 1
R0R1=(X2-X1)*(X-X1)+(Y2-Y1)*(Y-Y1)+(Z2-Z1)*(Z-Z1)
R0R2=(X2-X1)*(X-X2)+(Y2-Y1)*(Y-Y2)+(Z2-Z1)*(Z-Z2)
COEF=GAMA/(4.0*PAY*SQUARE)*(R0R1/R1-R0R2/R2)
U=R1R2X*COEF
V=R1R2Y*COEF
W=R1R2Z*COEF
GO TO 2
C WHEN POINT (X,Y,Z) LIES ON VORTEX ELEMENT; ITS INDUCED VELOCITY IS
1 U=0.
V=0.
W=0.
2 CONTINUE
RETURN
END
C
SUBROUTINE WING(X,Y,Z,GAMA,U,V,W,ONOFF,I1,J1)
DIMENSION GAMA(4,13),QF(6,14,3),A1(5,13)
DIMENSION DS(4,13,4)
COMMON/NO1/ DS
COMMON/NO2/ IB,JB,CH,SIGN
COMMON/NO3/ A1
COMMON/NO4/ QF
C
C CALCULATES INDUCED VELOCITY AT A POINT (X,Y,Z), DUE TO VORTICITY
C DISTRIBUTION GAMA(I,J), OF SEMI-CONFIGURATION - IN A WING FIXED
C COORDINATE SYSTEM.
U=0
V=0
W=0
IB1=IB+1
DO 1 I=1,IB1
DO 1 J=1,JB
C I3 IS WAKE VORTEX COUNTER
I3=I
IF(I.EQ.IB1) I3=IB
VORTIC=GAMA(I3,J)
IF(ONOFF.LT.0.1) GOTO 2
CALL VORTEX(X,Y,Z,QF(I,J,1),QF(I,J,2),QF(I,J,3),QF(I,J+1,1),QF(I,J
1+1,2),QF(I,J+1,3),VORTIC,U1,V1,W1)
CALL VORTEX(X,Y,Z,QF(I+1,J+1,1),QF(I+1,J+1,2),QF(I+1,J+1,3),
3QF(I+1,J,1),QF(I+1,J,2),QF(I+1,J,3),VORTIC,U3,V3,W3)
2 CALL VORTEX(X,Y,Z,QF(I,J+1,1),QF(I,J+1,2),QF(I,J+1,3),QF(I+1,J+1,1
2),QF(I+1,J+1,2),QF(I+1,J+1,3),VORTIC,U2,V2,W2)
CALL VORTEX(X,Y,Z,QF(I+1,J,1),QF(I+1,J,2),QF(I+1,J,3),QF(I,J,1),
4QF(I,J,2),QF(I,J,3),VORTIC,U4,V4,W4)
C
U0=U2+U4+(U1+U3)*ONOFF
V0=V2+V4+(V1+V3)*ONOFF
W0=W2+W4+(W1+W3)*ONOFF
A1(I,J)=U0*DS(I1,J1,1)+V0*DS(I1,J1,2)+W0*DS(I1,J1,3)
IF(SIGN.GE.1.0)
* A1(I,J)=U0*DS(I1,J1,1)+V0*DS(I1,J1,2)-W0*DS(I1,J1,3)
IF(I.EQ.IB1) A1(IB,J)=A1(IB,J)+A1(IB1,J)
U=U+U0
V=V+V0
W=W+W0
C
1 CONTINUE
RETURN
END
C
SUBROUTINE DECOMP(N,NDIM,A,IP)
REAL A(NDIM,NDIM),T
INTEGER IP(NDIM)
C MATRIX TRIANGULARIZATION BY GAUSSIAN ELIMINATION.
C N = ORDER OF MATRIX. NDIM = DECLARED DIMENSION OF ARRAY A.
C A = MATRIX TO BE TRIANGULARIZED.
C IP(K) , K .LT. N = INDEX OF K-TH PIVOT ROW.
C
IP(N) = 1
DO 6 K = 1, N
IF(K.EQ.N) GOTO 5
KP1 = K + 1
M = K
DO 1 I = KP1, N
IF( ABS(A(I,K)).GT.ABS(A(M,K))) M=I
1 CONTINUE
IP(K) = M
IF(M.NE.K) IP(N) = -IP(N)
T = A(M,K)
A(M,K) = A(K,K)
A(K,K) = T
IF(T.EQ.0.E0) GO TO 5
DO 2 I = KP1, N
2 A(I,K) = -A(I,K)/T
DO 4 J = KP1, N
T = A(M,J)
A(M,J) = A(K,J)
A(K,J) = T
IF(T .EQ. 0.E0) GO TO 4
DO 3 I = KP1, N
3 A(I,J) = A(I,J) + A(I,K)*T
4 CONTINUE
5 IF(A(K,K) .EQ. 0.E0) IP(N) = 0
6 CONTINUE
RETURN
END
C
SUBROUTINE SOLVER(N,NDIM,A,B,IP)
REAL A(NDIM,NDIM), B(NDIM), T
INTEGER IP(NDIM)
C SOLUTION OF LINEAR SYSTEM, A*X = B.
C N = ORDER OF MATRIX.
C NDIM = DECLARED DIMENSION OF THE ARRAY A.
C B = RIGHT HAND SIDE VECTOR.
C IP = PIVOT VECTOR OBTAINED FROM SUBROUTINE DECOMP.
C B = SOLUTION VECTOR, X.
C
IF(N.EQ.1) GOTO 9
NM1 = N - 1
DO 7 K = 1, NM1
KP1 = K + 1
M = IP(K)
T = B(M)
B(M) = B(K)
B(K) = T
DO 7 I = KP1, N
7 B(I) = B(I) + A(I,K)*T
DO 8 KB = 1, NM1
KM1 = N - KB
K = KM1 + 1
B(K) = B(K)/A(K,K)
T = -B(K)
DO 8 I = 1, KM1
8 B(I) = B(I) + A(I,K)*T
9 B(1) = B(1)/A(1,1)
RETURN
END
[-- Attachment #3: compilation.txt --]
[-- Type: text/plain, Size: 488 bytes --]
C:\Users\Jerome Huck\Desktop\VLM\vlm.f:235.17:
COMMON/NO1/ DS,X,B,C,S,AR,SN1,CS1
1
Warning: Named COMMON block 'no1' at (1) shall be of the same size as elsewhere (872 vs 832 bytes)
C:\Users\Jerome Huck\Desktop\VLM\vlm.f:237.17:
COMMON/NO4/ QF,QC,DXW
1
Warning: Named COMMON block 'no4' at (1) shall be of the same size as elsewhere (1636 vs 1008 bytes)
^ permalink raw reply [flat|nested] 2+ messages in thread
* Gfortran issue
@ 2008-09-18 14:21 Vardhan, Sundara (GE Infra, Energy)
0 siblings, 0 replies; 2+ messages in thread
From: Vardhan, Sundara (GE Infra, Energy) @ 2008-09-18 14:21 UTC (permalink / raw)
To: gcc-help
Hi All
I am compiling legacy fortran 77 code which used VAX-Fortran type
parameterized formats, in gfortran version as below :
Target: powerpc-ibm-aix5.3.0.0
Configured with: /cots/gnu/gcc-4.2.3/configure --prefix=/opt/freeware
--with-gmp=/usr/local --with-mpfr=/usr/local
--enable-languages=c,c++,fortran
Thread model: aix
gcc version 4.2.3
I have a fortran program having the following lines of code among
others. These lines of code is what generats a compile error :
CHARACTER*(24*RT_MB_MAXMB) PNTNAME
........
WRITE(LO,220)
220 FORMAT(A<24*RT_MB_MAXMB>)
The error I get is : Error: Unexpected element in format string at (1).
Is there any way to get around this in gfortran. Works fine in g77 but
does not in gfortran. Your help and advice and pointers will be greatly
appreciated.
With Regards
Vardhan
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