i use this code to sweep and calculate at different angle of attack
#!/usr/bin/env python
## \file Compute_polar.py
# \brief Python script for performing polar sweep.
# \author E Arad (based on T. Lukaczyk and F. Palacios script)
# \version 6.2.0 "Falcon"
#
# The current SU2 release has been coordinated by the
# SU2 International Developers Society <www.su2devsociety.org>
# with selected contributions from the open-source community.
#
# The main research teams contributing to the current release are:
# - Prof. Juan J. Alonso's group at Stanford University.
# - Prof. Piero Colonna's group at Delft University of Technology.
# - Prof. Nicolas R. Gauger's group at Kaiserslautern University of Technology.
# - Prof. Alberto Guardone's group at Polytechnic University of Milan.
# - Prof. Rafael Palacios' group at Imperial College London.
# - Prof. Vincent Terrapon's group at the University of Liege.
# - Prof. Edwin van der Weide's group at the University of Twente.
# - Lab. of New Concepts in Aeronautics at Tech. Institute of Aeronautics.
#
# Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon,
# Tim Albring, and the SU2 contributors.
#
# SU2 is free software; you can redistribute it and/or
# modify it under the terms of the GNU Lesser General Public
# License as published by the Free Software Foundation; either
# version 2.1 of the License, or (at your option) any later version.
#
# SU2 is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
# Lesser General Public License for more details.
#
# You should have received a copy of the GNU Lesser General Public
# License along with SU2. If not, see <http://www.gnu.org/licenses/>.
#
#
# Several combinations of angles are possible:
#------------------------------------------------
# 1. Polar-sweep in alpha per given phi ...... polarVar = aoa
# 2. Polar-sweep in alpha per given beta (side slip angle) ...... polarVar = aoa
# 3. Polar-sweep in phi per given alpha ...... polarVar = phi
# 4. Mach ramp (single values for alpha, phi or both permitted) ... polarVar = MachRampNumbers
#
# Note: Seting a list of both phi and beta is impossible
# For mach ramp you can specify alpha, phi (or both), but not a list of either of them
# make print(*args) function available in PY2.6+, does'nt work on PY < 2.6
from __future__ import print_function
# imports
import os, sys
from optparse import OptionParser
sys.path.append(os.environ['SU2_RUN'])
import SU2
import SU2.util.polarSweepLib as psl
import copy
import numpy as np
def main():
# Command Line Options
parser = OptionParser()
parser.add_option("-c", "--ctrl", dest="ctrlFile",
help="reads polar control parameters from FILE (default:polarCtrl.in) ",
metavar="FILE", default="polarCtrl.in")
parser.add_option("-n", "--partitions", dest="partitions", default=2,
help="number of PARTITIONS", metavar="PARTITIONS")
parser.add_option("-i", "--iterations", dest="iterations", default=-1,
help="number of ITERATIONS", metavar="ITERATIONS")
parser.add_option("-d", "--dimmension", dest="geomDim", default=2,
help="Geometry dimension (2 or 3)", metavar="geomDim")
parser.add_option("-w", "--Wind", action="store_true", dest="Wind", default=False,
help=" Wind system (default is body system")
parser.add_option("-v", "--Verbose", action="store_true", dest="verbose", default=False,
help=" Verbose printout (if activated)")
(options, args) = parser.parse_args()
options.partitions = int(options.partitions)
options.iterations = int(options.iterations)
options.geomDim = int(options.geomDim)
d2r = np.pi/180
#
sweepOption = []
sweepOption.append(' Polar sweep type: 1. Sweep in AOA per given roll angle')
sweepOption.append(' Polar sweep type: 2. Sweep in AOA per given sideslip-angle')
sweepOption.append(' Polar sweep type: 3. Sweep in phi per given AOA')
sweepOption.append(' Polar sweep type: 4. Mach ramp (single- value AOA and sideslip-angle')
#
#--------------- now read the parameters control file and parse it
fc = open(options.ctrlFile, 'r')
ctrl = fc.readlines()
nc = np.size(ctrl)
fc.close()
print(str(nc)+" lines read from control file: "+options.ctrlFile)
PA, polarSweepType, velDirOption, nAlpha, nBeta, nPhi, nMach, \
alpha, beta, phi, MachList, polarVar = \
psl.setPolaraType(ctrl, nc, options.verbose)
if options.verbose:
velDirOptionLegend = ['V(alpha,phi)', 'V(alpha,beta)']
print('>>> Control file details: Pitch axis is '+\
PA+'. Polar sweep type is '+str(polarSweepType)+\
'; polarVar = '+polarVar)
print('>>> Velocity definiton: '+velDirOptionLegend[velDirOption-1])
print('>>> nAalpha = '+str(nAlpha)+'; nBeta = '+str(nBeta)+\
'; nPhi = '+str(nPhi)+'; nMach = '+str(nMach))
if polarSweepType < 4:
nPolara = max(nAlpha, nPhi)
else:
nPolara = nMach
#-------------Configuration base file ----------------------
inputbaseFileString = 'input base file'
keyWordInputbaseFile = inputbaseFileString.lower()
iBaseInputF = psl.parLocator(keyWordInputbaseFile, ctrl, nc, -1, options.verbose)
bIFLine = ctrl[iBaseInputF]
icol = bIFLine.index(':')
sBIF = bIFLine[icol+1:]
inputbaseFile = sBIF.strip(' ')
inputbaseFile = inputbaseFile.strip('\n')
print(' ')
print('--------------------------------------------------------------------------------------')
print(' ')
print('Configuration file: ' + inputbaseFile)
print('PolarSweepType = '+str(polarSweepType)+' Polar sweep in '+polarVar+' using '+\
str(nPolara)+' angles/Mach No ')
print(' ')
print('--------------------------------------------------------------------------------------')
print(' ')
if polarSweepType == 4:
nPolara = 1 # prevent angles inner loop
if options.geomDim not in [2, 3]:
raise SystemExit('ERROR: dimension can be either 2 or 3 (-d parameter) ')
if options.Wind:
outSystem = 'Wind'
else:
outSystem = 'Body'
print(" ")
print("===============================================================================")
print(" Polar sweep in "+str(options.geomDim)+"D ; output in "+outSystem+" system")
print("===============================================================================")
print(" ")
# load config, start state
config = SU2.io.Config(inputbaseFile)
state = SU2.io.State()
# Set SU2 defaults units, if definitions are not included in the cfg file
if 'SYSTEM_MEASUREMENTS' not in config:
config.SYSTEM_MEASUREMENTS = 'SI'
if config.PHYSICAL_PROBLEM == 'NAVIER_STOKES':
if 'REYNOLDS_LENGTH' not in config:
config.REYNOLDS_LENGTH = 1.0
# prepare config
config.NUMBER_PART = options.partitions
if options.iterations > 0:
config.EXT_ITER = options.iterations
config.NZONES = 1
# find solution files if they exist
state.find_files(config)
# start results data
results = SU2.util.bunch()
if nMach == 0:
if 'MACH_NUMBER' in config:
MachList.append(config.MACH_NUMBER)
else:
MachList.append(0.5)
nMach = 1
if nAlpha == 0:
if 'AOA' in config:
alpha.append(config.AOA)
else:
alpha.append(0.0)
nAlpha = 1
if nPhi == 0:
phi.append(0.0)
nPhi = 1
noPhi_in_CTRL = True
else:
noPhi_in_CTRL = False
if nBeta == 0:
if noPhi_in_CTRL:
if 'SIDESLIP_ANGLE' in config:
beta.append(config.SIDESLIP_ANGLE)
else:
beta.append(0.0)
nBeta = 1
else:
if polarSweepType < 4: # alpha sweep with phi set
tAlpha = [np.tan(d2r*x) for x in alpha]
tPhi = [np.tan(d2r*x) for x in phi]
tb = [x*y for y in tAlpha for x in tPhi]
beta = [np.arctan(x)/d2r for x in tb]
nBeta = np.size(beta)
else: # Mach ramp
if 'SIDESLIP_ANGLE' in config:
beta.append(config.SIDESLIP_ANGLE)
else:
beta.append(0.0)
nBeta = 1
if options.verbose:
print('>>> alpha: '+str(alpha))
print('>>> beta: '+str(beta))
print('>>> phi: '+str(phi))
print('>>> Mach '+str(MachList))
results.AOA = alpha
results.MACH = MachList
results.SIDESLIP_ANGLE = beta
if options.geomDim == 3:
results.MOMENT_X = []
results.MOMENT_Y = []
if options.Wind:
results.DRAG = []
results.LIFT = []
if options.geomDim == 3:
results.SIDEFORCE = []
else:
results.FORCE_X = []
results.FORCE_Y = []
if options.geomDim == 3:
results.FORCE_Z = []
results.MOMENT_Z = []
if polarSweepType == 4:
outFile = 'machRamp_aoa' + str(alpha[0]) + '.dat'
else:
outFile = 'Polar_M' + str(MachList[0]) + '.dat'
bufsize = 12
#
#----------- Prepare output header ---------------
#
if config.SYSTEM_MEASUREMENTS == 'SI':
length_dimension = 'm'
else:
length_dimension = 'in'
f = open(outFile, 'w', bufsize)
if options.verbose:
print('Opening polar sweep file: ' + outFile)
f.write('% \n% Main coefficients for a polar sweep \n% \n% ')
f.write(sweepOption[polarSweepType-1])
if polarSweepType == 1:
satxt = ' ; Roll angle = %7.2f '%(phi[0])
elif polarSweepType == 2:
satxt = ' ; Sideslip angle = %7.2f '%(beta[0])
elif polarSweepType == 3:
satxt = ' ; AOA = %7.2f '%(alpha[0])
elif polarSweepType == 4:
satxt = ' ; AOA = %7.2f Side slip angle = %7.2f ; '%(alpha[0], beta[0])
f.write(satxt)
f.write('\n% \n')
f.write('% ================== Reference parameteres ======================\n%\n')
XR = config.REF_ORIGIN_MOMENT_X
YR = config.REF_ORIGIN_MOMENT_Y
ZR = config.REF_ORIGIN_MOMENT_Z
f.write('% Reference point for moments : [ ')
line_text = '%s , %s , %s ] [ %s ] '%(XR, YR, ZR, length_dimension)
f.write(line_text)
f.write('\n')
f.write('% Reference area and length: ')
line_text = 'Aref : %s Lref : %s [ %s ] '%(config.REF_AREA, config.REF_AREA, length_dimension)
f.write(line_text)
f.write('\n% ')
line_text = 'Mach : %7.2f , '%(config.MACH_NUMBER)
f.write(line_text)
if config.PHYSICAL_PROBLEM == 'NAVIER_STOKES':
line_text = 'Reynolds Number : %s '%(config.REYNOLDS_NUMBER)
f.write(line_text)
line_text = 'Reynolds length : %s [ %s ] '%(config.REYNOLDS_LENGTH, length_dimension)
else:
line_text = 'Physical problem : %s '%( config.PHYSICAL_PROBLEM)
f.write(line_text)
f.write('\n% ')
rho = float(config.FREESTREAM_PRESSURE)/\
(float(config.GAS_CONSTANT)*float(config.FREESTREAM_TEMPERATURE))
line_text = 'Reference pressure : %s ,'%(config.FREESTREAM_PRESSURE)
f.write(line_text)
line_text = ' Reference density : %7.4f , '%(rho)
f.write(line_text)
line_text = ' Reference Temperature : %s '%(config.FREESTREAM_TEMPERATURE)
f.write(line_text)
f.write('\n% ')
line_text = 'Constant specific heat ratio : %s , '%(config.GAMMA_VALUE)
f.write(line_text)
line_text = 'Gas constant : %s '%(config.GAS_CONSTANT)
f.write(line_text)
f.write('\n% ')
line_text = 'Grid file : %s '%(config.MESH_FILENAME)
f.write(line_text)
f.write('\n% ')
symmmetry_exists = False
if 'MARKER_SYM' in config:
if config.MARKER_SYM != 'NONE':
symmmetry_exists = True
if symmmetry_exists:
line_text = 'Symmetry surface : yes'
else:
line_text = 'Symmetry surface : no'
f.write(line_text)
f.write('\n% \n')
# ----------------- end reference parameter section --------------
if options.Wind:
f.write('% AOA, Mach, CL, CD, ')
if options.geomDim == 3:
f.write('CY, ')
else:
if options.geomDim == 2:
f.write('% AOA, Mach, CX, CY, ')
else:
f.write('% AOA, Mach, CX, CZ, CY, ')
if options.geomDim == 3:
f.write('Cmx, Cmz, Cmy \n')
else:
f.write(' Cmz \n')
firstSweepPoint = True
# iterate mach
for MachNumber in MachList:
# iterate angles
for j in range(0, nPolara):
if polarSweepType < 3:
AngleAttack = alpha[j]
SIDESLIP_ANGLE = beta[0]
elif polarSweepType == 3:
AngleAttack = alpha[0]
SIDESLIP_ANGLE = beta[j]
else:
AngleAttack = alpha[0]
SIDESLIP_ANGLE = beta[0]
if options.verbose:
print('Sweep step '+str(j)+': Mach = '+str(MachNumber)+\
', aoa = ', str(AngleAttack)+', beta = '+str(SIDESLIP_ANGLE))
# local config and state
konfig = copy.deepcopy(config)
# enable restart in polar sweep
konfig.DISCARD_INFILES = 'YES'
ztate = copy.deepcopy(state)
#
# The eval functions below requires definition of various optimization
# variables, though we are handling here only a direct solution.
# So, if they are missing in the cfg file (and only then), some dummy values are
# introduced here
if 'OBJECTIVE_FUNCTION' not in konfig:
konfig.OBJECTIVE_FUNCTION = 'DRAG'
if 'DV_KIND' not in konfig:
konfig.DV_KIND = ['FFD_SETTING']
if 'DV_PARAM' not in konfig:
konfig.DV_PARAM = {'FFDTAG': ['1'], 'PARAM': [[0.0, 0.5]], 'SIZE': [1]}
if 'DEFINITION_DV' not in konfig:
konfig.DEFINITION_DV = {'FFDTAG': [[]],
'KIND': ['HICKS_HENNE'],
'MARKER': [['WING']],
'PARAM': [[0.0, 0.05]],
'SCALE': [1.0],
'SIZE': [1]}
if 'OPT_OBJECTIVE' not in konfig:
obj = {}
obj['DRAG'] = {'SCALE':1.e-2, 'OBJTYPE':'DEFAULT', 'MARKER': 'None'}
konfig.OPT_OBJECTIVE = obj
#
# --------- end of dummy optimization variables definition section ---------
#
# set angle of attack and side-slip angle
konfig.AOA = AngleAttack
konfig.SIDESLIP_ANGLE = SIDESLIP_ANGLE
konfig.MACH_NUMBER = MachNumber
caseName = 'DIRECT_M_' + str(MachNumber) + '_AOA_' + str(AngleAttack)
print('Mach = ', konfig.MACH_NUMBER, 'AOA = ', konfig.AOA)
print('case :' + caseName)
if firstSweepPoint:
# if caseName exists copy the restart file from it for run continuation
# Continue from previous sweep point if this is not he first
if os.path.isdir(caseName):
command = 'cp '+caseName+'/'+config.SOLUTION_FLOW_FILENAME+' .'
if options.verbose:
print(command)
os.system(command)
konfig.RESTART_SOL = 'YES'
else:
konfig.RESTART_SOL = 'NO'
firstSweepPoint = False
else:
konfig.RESTART_SOL = 'YES'
if konfig.RESTART_SOL == 'YES':
ztate.FILES.DIRECT = config.SOLUTION_FLOW_FILENAME
# run su2
if options.Wind:
drag = SU2.eval.func('DRAG', konfig, ztate)
lift = SU2.eval.func('LIFT', konfig, ztate)
if options.geomDim == 3:
sideforce = SU2.eval.func('SIDEFORCE', konfig, ztate)
else:
force_x = SU2.eval.func('FORCE_X', konfig, ztate)
force_y = SU2.eval.func('FORCE_Y', konfig, ztate)
if options.geomDim == 3:
force_z = SU2.eval.func('FORCE_Z', konfig, ztate)
momentz = SU2.eval.func('MOMENT_Z', konfig, ztate)
if options.geomDim == 3:
momentx = SU2.eval.func('MOMENT_X', konfig, ztate)
momenty = SU2.eval.func('MOMENT_Y', konfig, ztate)
# append results
if options.Wind:
results.DRAG.append(drag)
results.LIFT.append(lift)
if options.geomDim == 3:
results.SIDEFORCE.append(sideforce)
else:
results.FORCE_X.append(force_x)
results.FORCE_Y.append(force_y)
if options.geomDim == 3:
results.FORCE_Z.append(force_z)
results.MOMENT_Z.append(momentz)
if options.geomDim == 3:
results.MOMENT_X.append(momentx)
results.MOMENT_Y.append(momenty)
output = ' ' + str(AngleAttack) + ", "+str(MachNumber)+", "
if options.Wind:
output = output+ str(lift) + ", " + str(drag)
if options.geomDim == 3:
output = output+", "+str(sideforce)
else:
if options.geomDim == 2:
output = output+ str(force_x) + ", " + str(force_y)
else:
output = output + str(force_x) + ", " + str(force_z) + ", " + str(force_y)
if options.geomDim == 3:
output = output + ", " + str(momentx) + ", " + str(momentz) + ", "
output = output + str(momenty) + " \n"
else:
output = output+", "+str(momentz)+" \n"
f.write(output)
# save data
SU2.io.save_data('results.pkl', results)
os.system('cp results.pkl DIRECT/.')
os.system('cp '+config.SOLUTION_FLOW_FILENAME+' DIRECT/.')
if os.path.isdir(caseName):
command = 'cat '+caseName+\
'/history_direct.dat DIRECT/history_direct.dat > tmp && mv tmp '+\
'DIRECT/history_direct.dat'
if options.verbose:
print(command)
os.system(command)
os.system('rm -R '+caseName)
command = 'cp -p -R DIRECT '+caseName
if options.verbose:
print(command)
os.system(command)
# Close open file
f.close()
if os.path.isdir('DIRECT'):
os.system('rm -R DIRECT')
if os.path.isfile(config.SOLUTION_FLOW_FILENAME):
os.system('rm '+config.SOLUTION_FLOW_FILENAME)
if os.path.isfile('results.pkl'):
os.system('rm results.pkl')
print('Post sweep cleanup completed')
# sys.exit(0)
#----------------------------------------------------------#
#: for each angle
# plotting
#plt.figure()
#plt.plot( results.MACH_NUMBER, results.AOA , results.LIFT , results.DRAG )
#plt.show()
if __name__ == "__main__":
main()
explain how i can use this code to do analysis which the file polarCtrl.in as following
# Control file for polar sweep run (default).
# Note that this file is currently set for the QuickStart NACA 0012 case.
Pitch axis : Z
# One of the following lists of values (> 1) given at a time.
angles of attack : 6.13779, 8.20698, 10.28034, 12.33281, 14.38945, 16.01136, 18.12235, 19.3137, 20.14555
# roll angles : 0.0, 45.0, 48.0, 50.0, 52.0, 55.0, 60.0, 90.0
# side slip angle : 3.0
# Mach ramp numbers : 0.3, 0.4, 0.6
input base file : SST_Incompressible.cfg
the file SST_Incompressible.cfg as following
%#############################################################################%
% %
% SU2 Configuration File %
% Incompressible Airfoil Shape Optimization %
% with SST Turbulence Model and Gamma-ReTheta Transition %
% %
%#############################################################################%
% -------------------- MAIN SOLVER AND PHYSICS DEFINITION --------------------%
% Solver for incompressible RANS equations
SOLVER= INC_RANS
% Use Menter's SST turbulence model
KIND_TURB_MODEL= SST
% Activate Langtry-Menter transition model
%KIND_TRANS_MODEL= LM
% Use the 2015 correlation for the LM model
%LM_OPTIONS= LM2015
% [DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT]
MATH_PROBLEM= DIRECT
% Set to CONTINUOUS_ADJOINT for gradient computation
RESTART_SOL= NO
% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
%
GAMMA_VALUE= 1.4
GAS_CONSTANT= 287.87
% ------------------------- REFERENCE VALUES ---------------------------------%
% Moment reference center (typically quarter-chord)
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.0
REF_ORIGIN_MOMENT_Z = 0.0
% Reference length (airfoil chord) [m]
REF_LENGTH= 1.0
% Reference area [m^2]
REF_AREA= 1.0
% Reference velocity [m/s] this for reynold number 1e7
REF_VELOCITY= 26.596
% Reference viscosity [kg/(m-s)]
REF_VISCOSITY= 1.0
% ----------------------- INCOMPRESSIBLE CONDITIONS --------------------------%
% Constant density model
INC_DENSITY_MODEL= CONSTANT
% Disable energy equation (isothermal flow)
INC_ENERGY_EQUATION= NO
% Non-dimensionalize using initial values
INC_NONDIM= INITIAL_VALUES
INC_DENSITY_INIT= 1.225
% Initial density (kg/m^3) - air at sea level
INC_TEMPERATURE_INIT= 288.15
% Initial velocity vector 26.596 (m/s) at angle of AOA= 4.9004
INC_VELOCITY_INIT= ( 26.58650267 , 0.71069827, 0.0 )
% ---------------- TURBULENCE & TRANSITION INITIALIZATION --------------------%
% Note: These are used even in incompressible flow for the turbulence model.
% Reynolds number based on chord
REYNOLDS_NUMBER= 1.8e6
% Freestream turbulence intensity (%)
FREESTREAM_TURBULENCEINTENSITY= 0.0015
% Initial intermittency (1 = fully turbulent)
FREESTREAM_INTERMITTENCY= 1.0
% Initial turb-to-lam viscosity ratio
FREESTREAM_TURB2LAMVISCRATIO= 0.1
% Surface roughness height for transition model [m]
HROUGHNESS= 1.0e-6
% ------------------------- BOUNDARY CONDITIONS ------------------------------%
MARKER_HEATFLUX= ( AIRFOIL, 0.0 )
MARKER_FAR= ( FARFIELD )
% ------------------------- SURFACE IDENTIFICATION ---------------------------%
% Surfaces to plot
MARKER_PLOTTING= ( AIRFOIL )
% Surfaces to monitor forces
MARKER_MONITORING= ( AIRFOIL )
% Surfaces to be modified during design
MARKER_DESIGNING= ( AIRFOIL )
% Surfaces for detailed analysis
MARKER_ANALYZE= ( AIRFOIL )
% ------------------------ NUMERICAL METHODS ---------------------------------%
MUSCL_TURB= NO
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
MUSCL_ADJFLOW= NO
SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
MUSCL_ADJTURB= NO
SLOPE_LIMITER_ADJTURB= VENKATAKRISHNAN
% Use higher-order reconstruction
MUSCL_FLOW= NO
ADJ_SHARP_LIMITER_COEFF= 3.0
LIMITER_ITER= 999999
LAX_SENSOR_COEFF= 0.15
JST_SENSOR_COEFF= ( 0.5, 0.02 )
ADJ_LAX_SENSOR_COEFF= 0.15
ADJ_JST_SENSOR_COEFF= ( 0.5, 0.02 )
% Spatial Discretization
% Convective scheme for flow
CONV_NUM_METHOD_FLOW= JST
% Convective scheme for turbulence eqns
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
% Gradient computation method
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
% Slope limiter for flow
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
% Limiter coefficient
VENKAT_LIMITER_COEFF= 0.05
% Temporal Discretization
% Implicit Euler time integration
TIME_DISCRE_FLOW= EULER_IMPLICIT
% Implicit Euler for turbulence
TIME_DISCRE_TURB= EULER_IMPLICIT
% Linear Solver
% Linear solver type
LINEAR_SOLVER= FGMRES
% Preconditioner type
LINEAR_SOLVER_PREC= ILU
% Linear solver tolerance
LINEAR_SOLVER_ERROR= 1E-4
% Max linear solver iterations
LINEAR_SOLVER_ITER= 10
% Multigrid
% Number of multigrid levels
MGLEVEL= 0
MGCYCLE= V_CYCLE
% Match MG_PRE/POST lengths to MGLEVEL+1 (levels: 0..MGLEVEL)
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
MG_DAMP_RESTRICTION= 0.8
MG_DAMP_PROLONGATION= 0.8
% ------------------------- CONVERGENCE PARAMETERS ---------------------------%
% Initial CFL number
CFL_NUMBER= 5.0
CFL_ADAPT= YES
% CFL adaptation parameters
% Reduce CFL for turbulence equations
%CFL_ADAPT_PARAM= (0.1, 1.2, 0.5, 50.0, 0.001, 100)
CFL_ADAPT_PARAM= (0.1, 1.2, 0.5, 50.0)
CFL_REDUCTION_TURB= 1.0
% Max inner iterations per time step
INNER_ITER= 20000
% Convergence criteria (log10 of residual)
CONV_RESIDUAL_MINVAL= -10
% Field to monitor for convergence
CONV_FIELD= DRAG ,LIFT
% Window size for Cauchy criteria
CONV_CAUCHY_ELEMS= 200
% Tolerance for Cauchy criteria
CONV_CAUCHY_EPS= 1E-5
% Start convergence checking after N iterations
CONV_STARTITER= 10
% ----------------------- TIME-DEPENDENT SIMULATION --------------------------%
% Steady-state simulation
TIME_DOMAIN= NO
% No time marching
TIME_MARCHING= NO
% ------------------------- FLUID PROPERTIES ---------------------------------%
% Fluid model for incompressible flow
FLUID_MODEL= CONSTANT_DENSITY
% Constant viscosity model
VISCOSITY_MODEL= CONSTANT_VISCOSITY
%# Dynamic viscosity (kg/m-s) for air at 15°C Dynamic viscosity of the fluid in kg/(m⋅s)
MU_CONSTANT= 1.81e-05
% ----------------------- OUTPUT CONFIGURATION -------------------------------%
SCREEN_OUTPUT= (INNER_ITER, WALL_TIME, RMS_RES, LIFT, DRAG, MOMENT_Z, SENS_GEO)
HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER)
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL, FLOW_COEFFS)
OUTPUT_FILES= (RESTART, PARAVIEW, SURFACE_PARAVIEW)
% Output frequencies
SCREEN_WRT_FREQ_INNER= 1
HISTORY_WRT_FREQ_INNER= 1
OUTPUT_WRT_FREQ= 100
WRT_FORCES_BREAKDOWN= YES
% File names
MESH_FILENAME= FFA-W3-211_StructMesh_RoundTE_RE1.8e6.su2
MESH_FORMAT= SU2
SOLUTION_FILENAME= solution_flow
RESTART_FILENAME= restart_flow
SOLUTION_ADJ_FILENAME= solution_adj
RESTART_ADJ_FILENAME= restart_adj
CONV_FILENAME= history
TABULAR_FORMAT= CSV
GRAD_OBJFUNC_FILENAME= of_grad
MESH_OUT_FILENAME= mesh_out.su2
VOLUME_FILENAME= flow
SURFACE_FILENAME= surface_flow
READ_BINARY_RESTART= YES
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