(m6wing.txt)  August 2002

   Number of blocks:      4
   Block:    1  ni,nj,nk:     25    49    33      40425
   Block:    2  ni,nj,nk:     73    49    33     118041
   Block:    3  ni,nj,nk:     73    49    33     118041
   Block:    4  ni,nj,nk:     25    49    33      40425
   Total number of grid points:                  316932

/bin/rm -rf run.cgd
cfcnvt < cfcnvt.x.com
gman < gman.a.com
gman < gman.b.com

!..Use flow2 to determine proper pressure to match Mach, Rec, and T.
 Flow Conditions
 ---------------
 Mach =                 0.8395000    
 Reynolds number    =   1.1720000E+07
 Reynolds number    =   2.1701412E+07  /ft
 Reference length   =   0.5400570      ft
 Static temperature =    460.0000      R
 Total temperature  =    524.8379      R
 Static pressure    =    6599.375      psf
 Static pressure    =    45.82899      psi
 Total pressure     =    10469.81      psf
 Total pressure     =    72.70699      psi
 Static density     =   8.3581228E-03  slug/ft^3
 Static density     =   0.2689143      lbm/ft^3
 Acoustic speed     =    1051.383      ft/sec
 Velocity           =    882.6362      ft/sec
 Total energy       =    19754.12      psf
 Laminar viscosity  =   3.3994013E-07  slug/ft-sec
 Dynamic viscosity  =   4.0671828E-05  ft^2/sec
 --- End of flow2 ---

!..Run WIND using data input file  m6wing.dat
wind -runinplace -dat run -mp -parallel

tail -200 run.lis

!..Residual of flow equations.
resplt < resplt.nsl2.com
cfpost < cfpost.nsl2.com

!..Residual of S-A turbulence equation.
resplt < resplt.sal2.com
cfpost < cfpost.sal2.com

!..Iteration history of lift.
resplt < resplt.liftconv.com
cfpost < cfpost.liftconv.com

!..Create PLOT3D files.
cfpost < cfpost.plot3d.com

!..Integrate forces on the wing.
cfpost < cfpost.forces.com
cat forces.lis

!..Make cut at z-station along wing span and write out Cp.

f77 readat.f -o readat
readat < ONERAb114.dat

f77 readgen.f -o readgen

cfpost < cfpost.zcut.cp1.com
readgen < cp1.gen
xmgr cp1.xm cp.do
mv cp.do cp1.do
xmgr cp1.ex cp1.do

cfpost < cfpost.zcut.cp2.com
readgen < cp2.gen
xmgr cp2.xm cp.do
mv cp.do cp2.do
xmgr cp2.ex cp2.do

cfpost < cfpost.zcut.cp3.com
readgen < cp3.gen
xmgr cp3.xm cp.do
mv cp.do cp3.do
xmgr cp3.ex cp3.do

cfpost < cfpost.zcut.cp4.com
readgen < cp4.gen
xmgr cp4.xm cp.do
mv cp.do cp4.do
xmgr cp4.ex cp4.do

cfpost < cfpost.zcut.cp5.com
readgen < cp5.gen
xmgr cp5.xm cp.do
mv cp.do cp5.do
xmgr cp5.ex cp5.do

cfpost < cfpost.zcut.cp6.com
readgen < cp6.gen
xmgr cp6.xm cp.do
mv cp.do cp6.do
xmgr cp6.ex cp6.do

cfpost < cfpost.zcut.cp7.com
readgen < cp7.gen
xmgr cp7.xm cp.do
mv cp.do cp7.do
xmgr cp7.ex cp7.do

!..Plot Mach contours at z-station along wing span.
cfpost < cfpost.zcut.mach.com

!..Compute and plot boundary layer properties along a j-line 
!..at I60, K1 of zone 3 (top of airfoil, aft of shock)
cfpost < cfpost.blan.com
~/cfdsys/blan/blan