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xoper.f
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C***********************************************************************
C Module: xoper.f
C
C Copyright (C) 2000 Mark Drela
C
C This program is free software; you can redistribute it and/or modify
C it under the terms of the GNU General Public License as published by
C the Free Software Foundation; either version 2 of the License, or
C (at your option) any later version.
C
C This program is distributed in the hope that it will be useful,
C but WITHOUT ANY WARRANTY; without even the implied warranty of
C MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
C GNU General Public License for more details.
C
C You should have received a copy of the GNU General Public License
C along with this program; if not, write to the Free Software
C Foundation, Inc., 675 Mass Ave, Cambridge, MA 02139, USA.
C***********************************************************************
C
SUBROUTINE OPER
INCLUDE 'XFOIL.INC'
CHARACTER*1 ANS
CHARACTER*4 COMAND, COMOLD
LOGICAL LRECALC, LCPX, LCONV
C
CHARACTER*128 COMARG, ARGOLD, LINE
C
PARAMETER (NPRX = 101)
DIMENSION XPR(NPRX), YPR(NPRX)
C
DIMENSION NBLP(NPX)
DIMENSION IPPAI(NPX), NAPOLT(NPX)
C
DIMENSION IINPUT(20)
DIMENSION RINPUT(20)
LOGICAL ERROR
C
C---- retain last-command info if OPER is exited and then re-entered
SAVE COMOLD, ARGOLD
C
C---- logical units for polar save file, polar dump file
LUPLR = 9
LUPLX = 11
C
COMAND = '****'
COMARG = ' '
LRECALC = .FALSE.
LCPX = .FALSE.
LPLOT = .FALSE.
LEXITFLAG = .FALSE.
C
IF(N.EQ.0) THEN
WRITE(*,*)
WRITE(*,*) '*** No airfoil available ***'
RETURN
ENDIF
C
IF(IPACT.NE.0) THEN
WRITE(*,5000) IPACT
5000 FORMAT(/' Polar', I3,' is active')
ENDIF
C
ccc 500 CONTINUE
COMOLD = COMAND
ARGOLD = COMARG
C
C====================================================
C******************************************************
C START OF DB COMMAND STRUCTURE
C
C Main purpose is to calculate Cl/Cd either
C through inviscid or viscous calculation.
C
c LVISC = .NOT. LVISC
LVISC = .TRUE.
C
c IF(LVISC) THEN
C IF(NINPUT.GE.1) THEN
C REINF1 = RINPUT(1)
C ELSE IF(REINF1 .EQ. 0.0) THEN
C CALL ASKR('Enter Reynolds number^',REINF1)
C ENDIF
C
C******************************************************
C REINF1 = 100000
C WRITE(*,*) REINF1
C STOP
C*****CHANGE REYNOLDS NUMBER***************************
C ITMAX = 75
C CALL MRSHOW(.TRUE.,.TRUE.)
c ENDIF
LCONV = .FALSE.
IF(.NOT.LRECALC) THEN
C------- set inviscid solution only if point is not being recalculated
C IF(NINPUT.GE.1) THEN
C ADEG = RINPUT(1)
C ELSE
C ADEG = ALFA/DTOR
C CALL ASKR('Enter angle of attack (deg)^',ADEG)
C ENDIF
C ADEG = 0.0 SET IN XFOIL.F NOW
LALFA = .TRUE.
ALFA = DTOR*ADEG
QINF = 1.0
CALL SPECAL
IF(ABS(ALFA-AWAKE) .GT. 1.0E-5) LWAKE = .FALSE.
IF(ABS(ALFA-AVISC) .GT. 1.0E-5) LVCONV = .FALSE.
IF(ABS(MINF-MVISC) .GT. 1.0E-5) LVCONV = .FALSE.
ENDIF
C
IF(LVISC) CALL VISCAL(ITMAX)
c return now if the VISCAL call failed
IF(LEXITFLAG) RETURN
C CALL CPX
CALL FCPMIN
C
C IF(LVISC .AND. LPACC .AND. LVCONV) THEN
C CALL PLRADD(LUPLR,IPACT)
C CALL PLXADD(LUPLX,IPACT)
C ENDIF
C
C IF(LVISC .AND. .NOT.LPACC .AND. .NOT.LVCONV) THEN
C WRITE(*,*) 'Type "!" to continue iterating'
C ENDIF
C call cpcalc(N+NW,QVIS,QINF,MINF,CPV)
call cdcalc
C CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF,XCMREF,YCMREF,
C & CL,CM,CDP, CL_ALF,CL_MSQ)
RETURN
C
END ! OPER
SUBROUTINE FCPMIN
C------------------------------------------------
C Finds minimum Cp on dist for cavitation work
C------------------------------------------------
INCLUDE 'XFOIL.INC'
C
XCPMNI = X(1)
XCPMNV = X(1)
CPMNI = CPI(1)
CPMNV = CPV(1)
C
DO I = 2, N + NW
IF(CPI(I) .LT. CPMNI) THEN
XCPMNI = X(I)
CPMNI = CPI(I)
ENDIF
IF(CPV(I) .LT. CPMNV) THEN
XCPMNV = X(I)
CPMNV = CPV(I)
ENDIF
ENDDO
C
IF(LVISC)THEN
CPMN = CPMNV
ELSE
CPMN = CPMNI
C
CPMNV = CPMNI
XCPMNV = XCPMNI
ENDIF
C
RETURN
END ! FCPMIN
SUBROUTINE MRSHOW(LM,LR)
INCLUDE 'XFOIL.INC'
LOGICAL LM, LR
C
IF(LM .OR. LR) WRITE(*,*)
C
IF(LM) THEN
IF(MATYP.EQ.1) WRITE(*,1100) MINF1
IF(MATYP.EQ.2) WRITE(*,1100) MINF1, ' / sqrt(CL)'
IF(MATYP.EQ.3) WRITE(*,1100) MINF1, ' / CL'
ENDIF
C
IF(LR) THEN
IF(RETYP.EQ.1) WRITE(*,1200) INT(REINF1)
IF(RETYP.EQ.2) WRITE(*,1200) INT(REINF1), ' / sqrt(CL)'
IF(RETYP.EQ.3) WRITE(*,1200) INT(REINF1), ' / CL'
ENDIF
C
RETURN
C
1100 FORMAT(1X,'M =' , F10.4, A)
1200 FORMAT(1X,'Re =' , I10 , A)
END ! MRSHOW
SUBROUTINE NAMMOD(NAME,KDEL,KMOD0)
CHARACTER*(*) NAME
C-------------------------------------------
C Requests new modified NAME with
C version number in brackets, e.g.
C NACA 0012 [5]
C
C If bracketed index exists in NAME,
C it is incremented by KDEL.
C If no bracketed index exists, it
C is added with initial value KMOD0,
C unless KMOD0 is negative in which
C case nothing is added.
C-------------------------------------------
CHARACTER*48 NAMDEF
C
CALL STRIP(NAME,NNAME)
KBRACK1 = INDEX(NAME,'[')
KBRACK2 = INDEX(NAME,']')
C
NAMDEF = NAME(1:NNAME)
C
IF(KBRACK1.NE.0 .AND.
& KBRACK2.NE.0 .AND. KBRACK2-KBRACK1.GT.1) THEN
C----- brackets exist... get number, (go get user's input on READ error)
READ(NAME(KBRACK1+1:KBRACK2-1),*,ERR=40) KMOD
KMOD = IABS(KMOD)
KMODP = MOD( KMOD+KDEL , 100 )
IF(KBRACK1.GE.2) THEN
NAME = NAME(1:KBRACK1-1)
ELSE
NAME = ' '
ENDIF
CALL STRIP(NAME,NNAME)
ELSEIF(KMOD0.GT.0) THEN
KMODP = MOD( KMOD0 , 100 )
ELSE
KMODP = 0
ENDIF
C
IF (KMODP.GE.10) THEN
NAMDEF = NAME(1:NNAME) // ' [ ]'
WRITE(NAMDEF(NNAME+3:NNAME+4),1020) KMODP
1020 FORMAT(I2)
ELSEIF(KMODP.GE. 1) THEN
NAMDEF = NAME(1:NNAME) // ' [ ]'
WRITE(NAMDEF(NNAME+3:NNAME+3),1025) KMODP
1025 FORMAT(I1)
ENDIF
C
40 WRITE(*,1040) NAMDEF
1040 FORMAT(/' Enter airfoil name or <return> for default: ',A)
READ(*,1000) NAME
1000 FORMAT(A)
IF(NAME .EQ. ' ') NAME = NAMDEF
C
RETURN
END ! NAMMOD
SUBROUTINE BLDUMP(FNAME1)
INCLUDE 'XFOIL.INC'
CHARACTER*(*) FNAME1
C
CHARACTER*80 FILDEF
C
1000 FORMAT(A)
C
IF(FNAME1(1:1).NE.' ') THEN
FNAME = FNAME1
ELSE
C----- no argument... get it somehow
IF(NPREFIX.GT.0) THEN
C------ offer default using existing prefix
FILDEF = PREFIX(1:NPREFIX) // '.bl'
WRITE(*,1100) FILDEF
1100 FORMAT(/' Enter filename: ', A)
READ(*,1000) FNAME
CALL STRIP(FNAME,NFN)
IF(NFN.EQ.0) FNAME = FILDEF
ELSE
C------ nothing available... just ask for filename
CALL ASKS('Enter filename^',FNAME)
ENDIF
ENDIF
C
LU = 19
OPEN(LU,FILE=FNAME,STATUS='UNKNOWN')
REWIND(LU)
C
WRITE(LU,1000)
& '# s x y Ue/Vinf Dstar Theta Cf'
C 1.23456 0.23451 0.23451 0.23451 0.012345 0.001234 0.004123
C
CALL COMSET
DO 10 I=1, N
IS = 1
IF(GAM(I) .LT. 0.0) IS = 2
C
IF(LIPAN .AND. LVISC) THEN
IF(IS.EQ.1) THEN
IBL = IBLTE(IS) - I + 1
ELSE
IBL = IBLTE(IS) + I - N
ENDIF
DS = DSTR(IBL,IS)
TH = THET(IBL,IS)
CF = TAU(IBL,IS)/(0.5*QINF**2)
ELSE
DS = 0.
TH = 0.
CF = 0.
ENDIF
UE = (GAM(I)/QINF)*(1.0-TKLAM) / (1.0 - TKLAM*(GAM(I)/QINF)**2)
C
WRITE(LU,8500) S(I), X(I), Y(I), UE, DS, TH, CF
8500 FORMAT(1X,4F9.5,3F10.6)
10 CONTINUE
C
IF(LWAKE) THEN
IS = 2
DO 20 I=N+1, N+NW
IBL = IBLTE(IS) + I - N
DS = DSTR(IBL,IS)
TH = THET(IBL,IS)
CF = 0.
UI = UEDG(IBL,IS)
UE = (UI/QINF)*(1.0-TKLAM) / (1.0 - TKLAM*(UI/QINF)**2)
C
WRITE(LU,8500) S(I), X(I), Y(I), UE, DS, TH, CF
20 CONTINUE
ENDIF
C
CLOSE(LU)
RETURN
END ! BLDUMP
SUBROUTINE CPDUMP(FNAME1)
INCLUDE 'XFOIL.INC'
CHARACTER*(*) FNAME1
C
CHARACTER*80 FILDEF
C
1000 FORMAT(A)
C
IF(FNAME1(1:1).NE.' ') THEN
FNAME = FNAME1
ELSE
C----- no argument... get it somehow
IF(NPREFIX.GT.0) THEN
C------ offer default using existing prefix
FILDEF = PREFIX(1:NPREFIX) // '.cp'
WRITE(*,1100) FILDEF
1100 FORMAT(/' Enter filename: ', A)
READ(*,1000) FNAME
CALL STRIP(FNAME,NFN)
IF(NFN.EQ.0) FNAME = FILDEF
ELSE
C------ nothing available... just ask for filename
CALL ASKS('Enter filename^',FNAME)
ENDIF
ENDIF
C
C
LU = 19
OPEN(LU,FILE=FNAME,STATUS='UNKNOWN')
REWIND(LU)
C
WRITE(LU,1000)
& '# x Cp '
C 0.23451 0.23451
C
CALL COMSET
C
BETA = SQRT(1.0 - MINF**2)
BFAC = 0.5*MINF**2 / (1.0 + BETA)
C
DO 10 I=1, N
CPINC = 1.0 - (GAM(I)/QINF)**2
DEN = BETA + BFAC*CPINC
CPCOM = CPINC / DEN
C
WRITE(LU,8500) X(I), CPCOM
8500 FORMAT(1X,2F9.5)
10 CONTINUE
C
CLOSE(LU)
RETURN
END ! CPDUMP
SUBROUTINE MHINGE
C----------------------------------------------------
C Calculates the hinge moment of the flap about
C (XOF,YOF) by integrating surface pressures.
C----------------------------------------------------
INCLUDE 'XFOIL.INC'
C
IF(.NOT.LFLAP) THEN
C
CALL GETXYF(X,XP,Y,YP,S,N, TOPS,BOTS,XOF,YOF)
LFLAP = .TRUE.
C
ELSE
C
C------ find top and bottom y at hinge x location
TOPS = XOF
BOTS = S(N) - XOF
CALL SINVRT(TOPS,XOF,X,XP,S,N)
CALL SINVRT(BOTS,XOF,X,XP,S,N)
C
ENDIF
C
TOPX = SEVAL(TOPS,X,XP,S,N)
TOPY = SEVAL(TOPS,Y,YP,S,N)
BOTX = SEVAL(BOTS,X,XP,S,N)
BOTY = SEVAL(BOTS,Y,YP,S,N)
C
C
HMOM = 0.
HFX = 0.
HFY = 0.
C
C---- integrate pressures on top and bottom sides of flap
DO 20 I=2, N
IF(S(I-1).GE.TOPS .AND. S(I).LE.BOTS) GO TO 20
C
DX = X(I) - X(I-1)
DY = Y(I) - Y(I-1)
XMID = 0.5*(X(I)+X(I-1)) - XOF
YMID = 0.5*(Y(I)+Y(I-1)) - YOF
IF(LVISC) THEN
PMID = 0.5*(CPV(I) + CPV(I-1))
ELSE
PMID = 0.5*(CPI(I) + CPI(I-1))
ENDIF
HMOM = HMOM + PMID*(XMID*DX + YMID*DY)
HFX = HFX - PMID* DY
HFY = HFY + PMID* DX
20 CONTINUE
C
C---- find S(I)..S(I-1) interval containing s=TOPS
DO I=2, N
IF(S(I).GT.TOPS) GO TO 31
ENDDO
C
31 CONTINUE
C---- add on top surface chunk TOPS..S(I-1), missed in the DO 20 loop.
DX = TOPX - X(I-1)
DY = TOPY - Y(I-1)
XMID = 0.5*(TOPX+X(I-1)) - XOF
YMID = 0.5*(TOPY+Y(I-1)) - YOF
IF(S(I) .NE. S(I-1)) THEN
FRAC = (TOPS-S(I-1))/(S(I)-S(I-1))
ELSE
FRAC = 0.
ENDIF
IF(LVISC) THEN
TOPP = CPV(I)*FRAC + CPV(I-1)*(1.0-FRAC)
PMID = 0.5*(TOPP+CPV(I-1))
ELSE
TOPP = CPI(I)*FRAC + CPI(I-1)*(1.0-FRAC)
PMID = 0.5*(TOPP+CPI(I-1))
ENDIF
HMOM = HMOM + PMID*(XMID*DX + YMID*DY)
HFX = HFX - PMID* DY
HFY = HFY + PMID* DX
C
C---- add on inside flap surface contribution from hinge to top surface
DX = XOF - TOPX
DY = YOF - TOPY
XMID = 0.5*(TOPX+XOF) - XOF
YMID = 0.5*(TOPY+YOF) - YOF
HMOM = HMOM + PMID*(XMID*DX + YMID*DY)
HFX = HFX - PMID* DY
HFY = HFY + PMID* DX
C
C---- find S(I)..S(I-1) interval containing s=BOTS
DO I=N, 2, -1
IF(S(I-1).LT.BOTS) GO TO 41
ENDDO
C
41 CONTINUE
C---- add on bottom surface chunk BOTS..S(I), missed in the DO 20 loop.
DX = X(I) - BOTX
DY = Y(I) - BOTY
XMID = 0.5*(BOTX+X(I)) - XOF
YMID = 0.5*(BOTY+Y(I)) - YOF
IF(S(I) .NE. S(I-1)) THEN
FRAC = (BOTS-S(I-1))/(S(I)-S(I-1))
ELSE
FRAC = 0.
ENDIF
IF(LVISC) THEN
BOTP = CPV(I)*FRAC + CPV(I-1)*(1.0-FRAC)
PMID = 0.5*(BOTP+CPV(I))
ELSE
BOTP = CPI(I)*FRAC + CPI(I-1)*(1.0-FRAC)
PMID = 0.5*(BOTP+CPI(I))
ENDIF
HMOM = HMOM + PMID*(XMID*DX + YMID*DY)
HFX = HFX - PMID* DY
HFY = HFY + PMID* DX
C
C---- add on inside flap surface contribution from hinge to bottom surface
DX = BOTX - XOF
DY = BOTY - YOF
XMID = 0.5*(BOTX+XOF) - XOF
YMID = 0.5*(BOTY+YOF) - YOF
HMOM = HMOM + PMID*(XMID*DX + YMID*DY)
HFX = HFX - PMID* DY
HFY = HFY + PMID* DX
C
C---- add on TE base thickness contribution
DX = X(1) - X(N)
DY = Y(1) - Y(N)
XMID = 0.5*(X(1)+X(N)) - XOF
YMID = 0.5*(Y(1)+Y(N)) - YOF
IF(LVISC) THEN
PMID = 0.5*(CPV(1)+CPV(N))
ELSE
PMID = 0.5*(CPI(1)+CPI(N))
ENDIF
HMOM = HMOM + PMID*(XMID*DX + YMID*DY)
HFX = HFX - PMID* DY
HFY = HFY + PMID* DX
C
RETURN
END ! MHINGE
SUBROUTINE VPAR
C---------------------------------------------
C Viscous parameter change menu routine.
C---------------------------------------------
INCLUDE 'XFOIL.INC'
CHARACTER*4 COMAND
CHARACTER*128 COMARG
C
DIMENSION IINPUT(20)
DIMENSION RINPUT(20)
LOGICAL ERROR
C
C
TURB = 100.0 * EXP( -(ACRIT + 8.43)/2.4 )
WRITE(*,1200) XSTRIP(1), XSTRIP(2), ACRIT, TURB, VACCEL
C
500 CONTINUE
CALL ASKC('..VPAR^',COMAND,COMARG)
C
DO I=1, 20
IINPUT(I) = 0
RINPUT(I) = 0.0
ENDDO
NINPUT = 20
CALL GETINT(COMARG,IINPUT,NINPUT,ERROR)
NINPUT = 20
CALL GETFLT(COMARG,RINPUT,NINPUT,ERROR)
C
IF(COMAND.EQ.' ') RETURN
IF(COMAND.EQ.'? ') GO TO 5
IF(COMAND.EQ.'SHOW') GO TO 10
IF(COMAND.EQ.'XTR ') GO TO 40
IF(COMAND.EQ.'N ') GO TO 50
IF(COMAND.EQ.'VACC') GO TO 70
IF(COMAND.EQ.'INIT') GO TO 80
C
WRITE(*,1000) COMAND
GO TO 500
C
5 WRITE(*,1050)
GO TO 500
C
10 TURB = 100.0 * EXP( -(ACRIT + 8.43)/2.4 )
WRITE(*,1200) XSTRIP(1), XSTRIP(2), ACRIT, TURB, VACCEL
GO TO 500
C
40 IF(NINPUT.GE.2) THEN
XSTRIP(1) = RINPUT(1)
XSTRIP(2) = RINPUT(2)
ELSE
CALL ASKR('Enter top side Xtrip/c^',XSTRIP(1))
CALL ASKR('Enter bottom side Xtrip/c^',XSTRIP(2))
ENDIF
LVCONV = .FALSE.
GO TO 500
C
50 IF(NINPUT.GE.1) THEN
ACRIT = RINPUT(1)
ELSE
CALL ASKR('Enter critical amplification ratio^',ACRIT)
ENDIF
LVCONV = .FALSE.
GO TO 500
C
70 IF(NINPUT.GE.1) THEN
VACCEL = RINPUT(1)
ELSE
CALL ASKR('Enter viscous acceleration parameter^',VACCEL)
ENDIF
GO TO 500
C
80 LBLINI = .NOT.LBLINI
IF(.NOT.LBLINI) WRITE(*,*) 'BLs will be initialized on next point'
IF( LBLINI) WRITE(*,*) 'BLs are assumed to be initialized'
IF(.NOT.LBLINI) LIPAN = .FALSE.
GO TO 500
C
C...................................................................
C
1000 FORMAT(1X,A4,' command not recognized. Type a "?" for list')
1050 FORMAT(
& /' <cr> Return to OPER menu'
& /' SHOW Display viscous parameters'
& /' XTR rr Change trip positions Xtr/c'
& /' N r Change critical amplification exponent Ncrit'
& /' VACC r Change Newton solution acceleration parameter'
& /' INIT BL initialization flag toggle')
1200 FORMAT(/' Xtr/c =', F8.4, ' top side'
& /' Xtr/c =', F8.4, ' bottom side'
& /' Ncrit =', F8.2, ' (', F6.3, ' % turb. level )'
& /' Vacc =', F8.4 )
END ! VPAR
SUBROUTINE SPECAL
C-----------------------------------
C Converges to specified alpha.
C-----------------------------------
INCLUDE 'XFOIL.INC'
REAL MINF_CLM, MSQ_CLM
C
C---- calculate surface vorticity distributions for alpha = 0, 90 degrees
IF(.NOT.LGAMU .OR. .NOT.LQAIJ) CALL GGCALC
C
COSA = COS(ALFA)
SINA = SIN(ALFA)
C
C---- superimpose suitably weighted alpha = 0, 90 distributions
DO 50 I=1, N
GAM(I) = COSA*GAMU(I,1) + SINA*GAMU(I,2)
GAM_A(I) = -SINA*GAMU(I,1) + COSA*GAMU(I,2)
50 CONTINUE
PSIO = COSA*GAMU(N+1,1) + SINA*GAMU(N+1,2)
C
CALL TECALC
CALL QISET
C
C---- set initial guess for the Newton variable CLM
CLM = 1.0
C
C---- set corresponding M(CLM), Re(CLM)
CALL MRCL(CLM,MINF_CLM,REINF_CLM)
CALL COMSET
C
C---- set corresponding CL(M)
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP, CL_ALF,CL_MSQ)
C
C---- iterate on CLM
DO 100 ITCL=1, 20
C
MSQ_CLM = 2.0*MINF*MINF_CLM
DCLM = (CL - CLM)/(1.0 - CL_MSQ*MSQ_CLM)
C
CLM1 = CLM
RLX = 1.0
C
C------ under-relaxation loop to avoid driving M(CL) above 1
DO 90 IRLX=1, 12
C
CLM = CLM1 + RLX*DCLM
C
C-------- set new freestream Mach M(CLM)
CALL MRCL(CLM,MINF_CLM,REINF_CLM)
C
C-------- if Mach is OK, go do next Newton iteration
IF(MATYP.EQ.1 .OR. MINF.EQ.0.0 .OR. MINF_CLM.NE.0.0) GO TO 91
C
RLX = 0.5*RLX
90 CONTINUE
91 CONTINUE
C
C------ set new CL(M)
CALL COMSET
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP,CL_ALF,CL_MSQ)
C
IF(ABS(DCLM).LE.1.0E-6) GO TO 110
C
100 CONTINUE
WRITE(*,*) 'SPECAL: Minf convergence failed'
110 CONTINUE
C
C---- set final Mach, CL, Cp distributions, and hinge moment
CALL MRCL(CL,MINF_CL,REINF_CL)
CALL COMSET
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP, CL_ALF,CL_MSQ)
CALL CPCALC(N,QINV,QINF,MINF,CPI)
IF(LVISC) THEN
CALL CPCALC(N+NW,QVIS,QINF,MINF,CPV)
CALL CPCALC(N+NW,QINV,QINF,MINF,CPI)
ELSE
CALL CPCALC(N,QINV,QINF,MINF,CPI)
ENDIF
IF(LFLAP) CALL MHINGE
C
RETURN
END ! SPECAL
SUBROUTINE SPECCL
C-----------------------------------------
C Converges to specified inviscid CL.
C-----------------------------------------
INCLUDE 'XFOIL.INC'
C
C---- calculate surface vorticity distributions for alpha = 0, 90 degrees
IF(.NOT.LGAMU .OR. .NOT.LQAIJ) CALL GGCALC
C
C---- set freestream Mach from specified CL -- Mach will be held fixed
CALL MRCL(CLSPEC,MINF_CL,REINF_CL)
CALL COMSET
C
C---- current alpha is the initial guess for Newton variable ALFA
COSA = COS(ALFA)
SINA = SIN(ALFA)
DO 10 I=1, N
GAM(I) = COSA*GAMU(I,1) + SINA*GAMU(I,2)
GAM_A(I) = -SINA*GAMU(I,1) + COSA*GAMU(I,2)
10 CONTINUE
PSIO = COSA*GAMU(N+1,1) + SINA*GAMU(N+1,2)
C
C---- get corresponding CL, CL_alpha, CL_Mach
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP, CL_ALF,CL_MSQ)
C
C---- Newton loop for alpha to get specified inviscid CL
DO 100 ITAL=1, 20
C
DALFA = (CLSPEC - CL) / CL_ALF
RLX = 1.0
C
ALFA = ALFA + RLX*DALFA
C
C------ set new surface speed distribution
COSA = COS(ALFA)
SINA = SIN(ALFA)
DO 40 I=1, N
GAM(I) = COSA*GAMU(I,1) + SINA*GAMU(I,2)
GAM_A(I) = -SINA*GAMU(I,1) + COSA*GAMU(I,2)
40 CONTINUE
PSIO = COSA*GAMU(N+1,1) + SINA*GAMU(N+1,2)
C
C------ set new CL(alpha)
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP,CL_ALF,CL_MSQ)
C
IF(ABS(DALFA).LE.1.0E-6) GO TO 110
100 CONTINUE
WRITE(*,*) 'SPECCL: CL convergence failed'
110 CONTINUE
C
C---- set final surface speed and Cp distributions
CALL TECALC
CALL QISET
IF(LVISC) THEN
CALL CPCALC(N+NW,QVIS,QINF,MINF,CPV)
CALL CPCALC(N+NW,QINV,QINF,MINF,CPI)
ELSE
CALL CPCALC(N,QINV,QINF,MINF,CPI)
ENDIF
IF(LFLAP) CALL MHINGE
C
RETURN
END ! SPECCL
SUBROUTINE VISCAL(NITER1)
C----------------------------------------
C Converges viscous operating point
C----------------------------------------
INCLUDE 'XFOIL.INC'
C
C---- convergence tolerance
DATA EPS1 / 1.0E-10 /
C
NITER = NITER1
C
C---- calculate wake trajectory from current inviscid solution if necessary
IF(.NOT.LWAKE) THEN
CALL XYWAKE
ENDIF
C
C---- set velocities on wake from airfoil vorticity for alpha=0, 90
CALL QWCALC
C
C---- set velocities on airfoil and wake for initial alpha
CALL QISET
C
IF(.NOT.LIPAN) THEN
C
IF(LBLINI) CALL GAMQV
C
C----- locate stagnation point arc length position and panel index
CALL STFIND
C
C----- set BL position -> panel position pointers
CALL IBLPAN
c quit if the boundary layer array overflows
IF(LEXITFLAG) RETURN
C
C----- calculate surface arc length array for current stagnation point location
CALL XICALC
C
C----- set BL position -> system line pointers
CALL IBLSYS
C
ENDIF
C
C---- set inviscid BL edge velocity UINV from QINV
CALL UICALC
C
IF(.NOT.LBLINI) THEN
C
C----- set initial Ue from inviscid Ue
DO IBL=1, NBL(1)
UEDG(IBL,1) = UINV(IBL,1)
ENDDO
C
DO IBL=1, NBL(2)
UEDG(IBL,2) = UINV(IBL,2)
ENDDO
C
ENDIF
C
IF(LVCONV) THEN
C----- set correct CL if converged point exists
CALL QVFUE
IF(LVISC) THEN
CALL CPCALC(N+NW,QVIS,QINF,MINF,CPV)
CALL CPCALC(N+NW,QINV,QINF,MINF,CPI)
ELSE
CALL CPCALC(N,QINV,QINF,MINF,CPI)
ENDIF
CALL GAMQV
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP, CL_ALF,CL_MSQ)
CALL CDCALC
ENDIF
C
C---- set up source influence matrix if it doesn't exist
IF(.NOT.LWDIJ .OR. .NOT.LADIJ) CALL QDCALC
C
C---- Newton iteration for entire BL solution
IF(NITER.EQ.0) CALL ASKI('Enter number of iterations^',NITER)
C WRITE(*,*)
C WRITE(*,*) 'Solving BL system ...'
DO 1000 ITER=1, NITER
C
C------ fill Newton system for BL variables
c WRITE (*,*) 'Calling SETBL...'
CALL SETBL
c------ DB 040306
c WRITE (*,*) 'Exit flag = ', LEXITFLAG
IF (LEXITFLAG) THEN
WRITE(*,*) 'LEXITFLAG TRUE, GOING TO 90...'
GOTO 90
c WRITE(*,*) 'Exiting on account of test...'
c STOP
ENDIF
C
C------ solve Newton system with custom solver
c WRITE(*,*) 'CALLING BLSOLV...'
CALL BLSOLV
C
C------ update BL variables
CALL UPDATE
C
IF(LALFA) THEN
C------- set new freestream Mach, Re from new CL
CALL MRCL(CL,MINF_CL,REINF_CL)
CALL COMSET
ELSE
C------- set new inviscid speeds QINV and UINV for new alpha
CALL QISET
CALL UICALC
ENDIF
C
C------ calculate edge velocities QVIS(.) from UEDG(..)
CALL QVFUE
C
C------ set GAM distribution from QVIS
CALL GAMQV
C
C------ relocate stagnation point
CALL STMOVE
C
C------ set updated CL,CD
CALL CLCALC(N,X,Y,GAM,GAM_A,ALFA,MINF,QINF, XCMREF,YCMREF,
& CL,CM,CDP,CL_ALF,CL_MSQ)
CALL CDCALC
C
C------ display changes and test for convergence
IF (PRINTCONV) THEN
IF(RLX.LT.1.0)
& WRITE(*,2000) ITER, RMSBL, RMXBL, VMXBL,IMXBL,ISMXBL,RLX
IF(RLX.EQ.1.0)
& WRITE(*,2010) ITER, RMSBL, RMXBL, VMXBL,IMXBL,ISMXBL
CDP = CD - CDF
WRITE(*,2020) ALFA/DTOR, CL, CM, CD, CDF, CDP
ENDIF
C
IF(RMSBL .LT. EPS1) THEN
LVCONV = .TRUE.
AVISC = ALFA
MVISC = MINF
GO TO 90
ENDIF
C
1000 CONTINUE
C WRITE(*,*) 'VISCAL: Convergence failed'
C
90 CONTINUE
CALL CPCALC(N+NW,QINV,QINF,MINF,CPI)
CALL CPCALC(N+NW,QVIS,QINF,MINF,CPV)
IF(LFLAP) CALL MHINGE
RETURN
C....................................................................
2000 FORMAT
& (/1X,I3,' rms: ',ES10.4E2,' max: ',ES11.4E2,
& 3X,A1,' at ',I4,I3, ' RLX:',F6.3)
2010 FORMAT
& (/1X,I3,' rms: ',ES10.4E2,' max: ',ES11.4E2,
& 3X,A1,' at ',I4,I3)
2020 FORMAT
& ( 1X,3X,' a =', F9.5,' CL =',F9.5 /
& 1X,3X,' Cm =', F9.5,' CD =',F9.5,
& ' => CDf =',F9.5,' CDp =',F9.5)
END ! VISCAL
subroutine dcpout
include 'XFOIL.INC'
c
c Computes and writes upper and lower-surface
c Cp values at two specified x locations
c
c
x1 = 0.05
x2 = 0.15
c
lu = 60
open(lu,file='dcp.out',status='old',access='append',err=10)
go to 20
c
10 continue
open(lu,file='dcp.out',status='new')
write(lu,*) '# ', name
write(lu,*) '# alpha CL ',
& ' Cpl05 Cpu05 dCp05 ',
& ' Cpl15 Cpu15 dCp15 '
20 continue
c
call spline(cpv,w1,s,n)
c
su1 = sle + x1*(s(1)-sle)
sl1 = sle + x1*(s(n)-sle)
su2 = sle + x2*(s(1)-sle)
sl2 = sle + x2*(s(n)-sle)
c
call sinvrt(sl1,x1,x,xp,s,n)
call sinvrt(su1,x1,x,xp,s,n)
call sinvrt(sl2,x2,x,xp,s,n)
call sinvrt(su2,x2,x,xp,s,n)
c
cpl1 = seval(sl1,cpv,w1,s,n)
cpu1 = seval(su1,cpv,w1,s,n)
cpl2 = seval(sl2,cpv,w1,s,n)
cpu2 = seval(su2,cpv,w1,s,n)
c
write(lu,1200) alfa/dtor, cl,
& cpl1, cpu1, cpl1-cpu1,
& cpl2, cpu2, cpl2-cpu2