config['MG_DAMP_RESTRICTION'] = str(.4)
config['MG_DAMP_PROLONGATION'] = str(.4)
ouputF = open(WORKING_DIR + '/' + 'convergenceResult.txt', 'w')
ouputF.write('innerMeshSize,outerMeshSize,CL,CD,CM,E,Iterations,Time(min)\n')
projectName = 'cfdTest_' + datetime.now().strftime('%Y-%m-%d_%H_%M_%S')
projectDir = WORKING_DIR + '/' + projectName
#create project dir if necessary
if not os.path.isdir(projectDir):
os.mkdir(projectDir)
cfd = CFDrun(projectName, used_cores=SU2_USED_CORES)
#cfd.load_airfoil_from_file(INPUT_DIR + '/naca641-212.csv')
cfd.load_airfoil_from_file(INPUT_DIR + '/bzTest.dat')
cfd.c2d.pointsInNormalDir = 80
cfd.c2d.pointNrAirfoilSurface = 200
#cfd.c2d.farfieldRadius = 50.
cfd.c2d.reynoldsNum = REYNOLD
#cfd.c2d.farfieldRadius = 50.
#cfd.c2d.pointsInNormalDir = 120
cfd.construct2d_generate_mesh(scale=SCALE, wake_extension=0, plot=True)
cfd.su2_fix_mesh()
cfd.su2_solve(config)
results = cfd.su2_parse_iteration_result()
totalCL = results['CL']
totalCD = results['CD']
ouputF = open(WORKING_DIR + '/' + 'machResult_' + datetime.now().strftime('%Y-%m-%d_%H_%M_%S') + '.csv', 'w')
ouputF.write('machNr,AOA,CL,CD,CM,E,Iterations,Time(min)\n')
for mach in MACH_NR:
projectName = 'analysis_mach_%0.3f' % (mach)
projectDir = WORKING_DIR + '/' + projectName
#create project dir if necessary
if not os.path.isdir(projectDir):
os.mkdir(projectDir)
cfd = CFDrun(projectName, used_cores=SU2_USED_CORES)
cfd.load_airfoil_from_file(INPUT_DIR + '/vfw-va2.dat')
#cfd.construct2d_generate_mesh(scale=REF_LENGTH)
cfd.gmsh_generate_mesh(scale=REF_LENGTH)
cfd.su2_fix_mesh()
config['MACH_NUMBER'] = str(mach)
cfd.su2_solve(config)
results = cfd.su2_parse_iteration_result()
cfd.clean_up()
print('totalCL: ' + str(results['CL']))
print('totalCD: ' + str(results['CD']))
ouputF.write(str(mach / 100.) + ','
+ str(results['AOA']) + ','
def run_convergence_analysis_construct2d():
config = dict()
config['PHYSICAL_PROBLEM'] = 'EULER'
config['MACH_NUMBER'] = str(0.65)
config['AOA'] = str(0.)
config['FREESTREAM_PRESSURE'] = str(24999.8) # for altitude 10363 m
config['FREESTREAM_TEMPERATURE'] = str(220.79) # for altitude 10363 m
# config['GAS_CONSTANT'] = str(287.87)
# config['REF_LENGTH'] = str(1.0)
# config['REF_AREA'] = str(1.0)
config['MARKER_EULER'] = '( airfoil )'
config['MARKER_FAR'] = '( farfield )'
config['EXT_ITER'] = str(1000)
config['OUTPUT_FORMAT'] = 'PARAVIEW'
config['MG_DAMP_RESTRICTION'] = str(0.75)
config['MG_DAMP_PROLONGATION'] = str(0.75)
#for construct 2d
normalMeshDivider = [100] #range(60, 500, 10)
secondParam = [250]
cdList = np.zeros((len(normalMeshDivider), len(secondParam)))
clList = np.zeros((len(normalMeshDivider), len(secondParam)))
cmList = np.zeros((len(normalMeshDivider), len(secondParam)))
eList = np.zeros((len(normalMeshDivider), len(secondParam)))
ouputF = open(WORKING_DIR + '/' + 'convergenceResult.txt', 'w')
ouputF.write(
'innerMeshSize,outerMeshSize,CL,CD,CM,E,Iterations,Time(min)\n')
for iI in range(0, len(normalMeshDivider)):
for iO in range(0, len(secondParam)):
projectName = 'nacaMesh_i%06d_o%06d' % (int(
normalMeshDivider[iI]), int(secondParam[iO]))
projectDir = WORKING_DIR + '/' + projectName
#create project dir if necessary
if not os.path.isdir(projectDir):
os.mkdir(projectDir)
cfd = CFDrun(projectName, used_cores=SU2_USED_CORES)
cfd.load_airfoil_from_file(INPUT_DIR + '/naca641-212.csv')
cfd.c2d.pointsInNormalDir = normalMeshDivider[iI]
#cfd.gmsh.outerMeshSize = outerMeshSize[iO]
#cfd.gmsh_generate_mesh()
cfd.construct2d_generate_mesh()
cfd.su2_fix_mesh()
cfd.su2_solve(config)
results = cfd.su2_parse_iteration_result()
#totalCL, totalCD, totalCM, totalE = cfd.su2_parse_results()
totalCL = results['CL']
totalCD = results['CD']
totalCM = results['CMz']
totalE = results['CL/CD']
clList[iI][iO] = totalCL
cdList[iI][iO] = totalCD
cmList[iI][iO] = totalCM
eList[iI][iO] = totalE
ouputF.write(
str(normalMeshDivider[iI]) + ',' + str(secondParam[iO]) + ',' +
str(totalCL) + ',' + str(totalCD) + ',' + str(totalCM) + ',' +
str(totalE) + ',' + str(results['Iteration']) + ',' +
str(results['Time(min)']) + '\n')
ouputF.flush()
print('totalCL: ' + str(totalCL))
print('totalCD: ' + str(totalCD))
print('iI: ' + str(iI) + ' iO: ' + str(iO))
ouputF.close()
plt.pcolor(normalMeshDivider, secondParam, clList)
plt.colorbar()
plt.show()
print('done')
outputF = open(
WORKING_DIR + '/' + 'aoaResult_' +
datetime.now().strftime('%Y-%m-%d_%H_%M_%S') + '.csv', 'w')
outputF.write('machNr,AOA,CL,CD,CM,E,Iterations,Time(min)\n')
for a in AOA:
projectName = 'analysis_aoa_%0.4f' % (a)
projectDir = WORKING_DIR + '/' + projectName
#create project dir if necessary
if not os.path.isdir(projectDir):
os.mkdir(projectDir)
cfd = CFDrun(projectName, used_cores=SU2_USED_CORES)
cfd.load_airfoil_from_file(INPUT_DIR + '/airfoil.dat')
#cfd.load_airfoil_from_file(INPUT_DIR + '/vfw-va2.dat')
cfd.c2d.pointsInNormalDir = 80
cfd.c2d.pointNrAirfoilSurface = 200
cfd.c2d.reynoldsNum = REYNOLD
cfd.construct2d_generate_mesh(scale=SCALE, plot=False)
#cfd.gmsh_generate_mesh(scale=REF_LENGTH)
cfd.su2_fix_mesh()
config['AOA'] = str(a)
cfd.su2_solve(config)
results = cfd.su2_parse_iteration_result()
cfd.clean_up()
print('totalCL: ' + str(results['CL']))