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Commit ab8dfb9e authored by Paul Dechamps's avatar Paul Dechamps :speech_balloon:
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(feat) SU2 iterating 

However the solution seems only slightly affected by the blowing velocity computed.
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blast/interfaces/su2/SU2Interface.py
+ 114
− 89
View file @ ab8dfb9e
...@@ -30,6 +30,9 @@ class SU2Interface(SolversInterface): ...@@ -30,6 +30,9 @@ class SU2Interface(SolversInterface):
self.verbose = su2config.get('Verb', 0) self.verbose = su2config.get('Verb', 0)
self.have_mpi, self.comm, self.status, self.myid = self.__setup_mpi() self.have_mpi, self.comm, self.status, self.myid = self.__setup_mpi()
self.solver = pysu2.CSinglezoneDriver(self.filename, 1, self.comm) self.solver = pysu2.CSinglezoneDriver(self.filename, 1, self.comm)
self.comm.barrier()
# run solver
self.solver.Preprocess(0)
self.wingMarkersToID = {key: i for i, key in enumerate(self.solver.GetMarkerTags())} self.wingMarkersToID = {key: i for i, key in enumerate(self.solver.GetMarkerTags())}
self.wingTags = su2config.get('wingTags') self.wingTags = su2config.get('wingTags')
...@@ -53,36 +56,70 @@ class SU2Interface(SolversInterface): ...@@ -53,36 +56,70 @@ class SU2Interface(SolversInterface):
return have_mpi, comm, status, myid return have_mpi, comm, status, myid
def run(self): def run(self):
print('SU2Interface::Running SU2 solver.')
#Remove output in the terminal #Remove output in the terminal
if self.getVerbose() == 0: if self.getVerbose() == 0:
sys.stdout = open(os.devnull, 'w') sys.stdout = open(os.devnull, 'w')
self.comm.barrier()
# run solver
self.solver.Preprocess(0)
self.solver.Run() self.solver.Run()
self.solver.Postprocess() self.solver.Postprocess()
# write outputs # write outputs
self.solver.Monitor(0) self.solver.Monitor(0)
self.solver.Output(0) self.solver.Output(0)
self.comm.barrier() self.comm.barrier()
print(f'SU2Interface::SU2 solver finished in {self.solver.GetOutputValue("INNER_ITER"):.0f} iterations. RMS_DENSITY: {self.solver.GetOutputValue("RMS_DENSITY"):.2f}')
#restore stdout #restore stdout
if self.getVerbose() == 0: if self.getVerbose() == 0:
sys.stdout = sys.__stdout__ sys.stdout = sys.__stdout__
print(f'SU2Interface::SU2 solver finished in {self.solver.GetOutputValue("INNER_ITER"):.0f} iterations. RMS_DENSITY: {self.solver.GetOutputValue("RMS_DENSITY"):.2f}')
return 1 return 1
def writeCp(self, sfx=''): def writeCp(self, sfx=''):
""" Write Cp distribution around the airfoil on file. """ Write Cp distribution around the airfoil on file.
""" """
pass
def getCp(self): #GEt farfield pressure, velocity and density
cp = np.zeros((self.nPoints[0], 2)) vel_x_idx = self.solver.GetPrimitiveIndices()["VELOCITY_X"]
for i in range(len(self.iBnd[0].nodesCoord[:,0])): vel_y_idx = self.solver.GetPrimitiveIndices()["VELOCITY_Y"]
cp[i, 0] = self.iBnd[0].nodesCoord[i,0] pressure_idx = self.solver.GetPrimitiveIndices()["PRESSURE"]
cp[i, 1] = self.solver.GetVertexCp(int(self.bndMarkers[0]), int(self.iBnd[0].connectListNodes[i])) density_idx = self.solver.GetPrimitiveIndices()["DENSITY"]
return cp
nNodes_farfield = self.solver.GetNumberMarkerNodes(self.wingMarkersToID['farfield'])
velocity_farfield = np.zeros(nNodes_farfield)
pressure_farfield = np.zeros(nNodes_farfield)
density_farfield = np.zeros(nNodes_farfield)
primitives = self.solver.Primitives()
for inode in range(nNodes_farfield):
nodeIndex = self.solver.GetMarkerNode(self.wingMarkersToID['farfield'], inode)
# Velocity
vel_x = primitives.Get(nodeIndex, vel_x_idx)
vel_y = primitives.Get(nodeIndex, vel_y_idx)
velocity_farfield[inode] = np.sqrt(vel_x**2 + vel_y**2)
# Pressure
pressure_farfield[inode] = primitives.Get(nodeIndex, pressure_idx)
# Density
density_farfield[inode] = primitives.Get(nodeIndex, density_idx)
ref_pressure = np.mean(pressure_farfield)
ref_velocity = np.mean(velocity_farfield)
ref_density = np.mean(density_farfield)
cp = np.empty(0, dtype=float)
for body in self.iBnd:
for reg in body:
for inode, nodeIndexFloat in enumerate(reg.nodesCoord[:,-1]):
nodeIndex = int(nodeIndexFloat)
pressure = self.solver.Primitives().Get(nodeIndex, pressure_idx)
cp = np.append(cp, (pressure - ref_pressure)/(1/2*ref_density*ref_velocity**2))
np.savetxt(f'Cp{sfx}.dat', np.column_stack((self.iBnd[0][0].nodesCoord[:, 0], cp)))
# from matplotlib import pyplot as plt
# import matplotlib
# matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting
# plt.figure()
# plt.plot(self.iBnd[0][0].nodesCoord[:, 0], cp, 'x--')
# plt.xlabel('$x$')
# plt.ylabel('$c_p$')
# plt.gca().invert_yaxis()
# plt.savefig(f'cp{sfx}.png') # Save the plot as an image file
# print(f'Plot saved as cp{sfx}.png')
def save(self, writer): def save(self, writer):
pass pass
...@@ -131,7 +168,8 @@ class SU2Interface(SolversInterface): ...@@ -131,7 +168,8 @@ class SU2Interface(SolversInterface):
return self.verbose return self.verbose
def reset(self): def reset(self):
print('SU2Interface::Warning: Cannot reset solver.') if self.getVerbose() > 0:
print('SU2Interface::Warning: Cannot reset solver.')
pass pass
def getInviscidBC(self): def getInviscidBC(self):
...@@ -143,7 +181,7 @@ class SU2Interface(SolversInterface): ...@@ -143,7 +181,7 @@ class SU2Interface(SolversInterface):
- couplIter (int): Coupling iteration. - couplIter (int): Coupling iteration.
""" """
print('SU2Interface::Imposing inviscid boundary conditions.') # print('SU2Interface::Imposing inviscid boundary conditions.')
if self.getnDim() == 2: if self.getnDim() == 2:
velComponents = ['VELOCITY_X', 'VELOCITY_Y'] velComponents = ['VELOCITY_X', 'VELOCITY_Y']
elif self.getnDim() == 3: elif self.getnDim() == 3:
...@@ -159,7 +197,7 @@ class SU2Interface(SolversInterface): ...@@ -159,7 +197,7 @@ class SU2Interface(SolversInterface):
for body in self.iBnd: for body in self.iBnd:
for reg in body: for reg in body:
print('SU2Interface::Imposing inviscid boundary conditions on', reg.name) #print('SU2Interface::Imposing inviscid boundary conditions on', reg.name)
for inode, nodeIndexFloat in enumerate(reg.nodesCoord[:,-1]): for inode, nodeIndexFloat in enumerate(reg.nodesCoord[:,-1]):
nodeIndex = int(nodeIndexFloat) nodeIndex = int(nodeIndexFloat)
# Velocity # Velocity
...@@ -178,78 +216,67 @@ class SU2Interface(SolversInterface): ...@@ -178,78 +216,67 @@ class SU2Interface(SolversInterface):
self.iBnd[0][0].Rho[-1] = self.iBnd[0][0].Rho[-2] self.iBnd[0][0].Rho[-1] = self.iBnd[0][0].Rho[-2]
self.iBnd[0][0].M[0] = self.iBnd[0][0].M[-2] self.iBnd[0][0].M[0] = self.iBnd[0][0].M[-2]
self.iBnd[0][0].M[-1] = self.iBnd[0][0].M[-2] self.iBnd[0][0].M[-1] = self.iBnd[0][0].M[-2]
print('vel first', self.iBnd[0][0].V[0,:]) # print('vel first', self.iBnd[0][0].V[0,:])
print('Rho first', self.iBnd[0][0].Rho[0]) # print('Rho first', self.iBnd[0][0].Rho[0])
print('M first', self.iBnd[0][0].M[0]) # print('M first', self.iBnd[0][0].M[0])
print('vel last', self.iBnd[0][0].V[-1,:]) # print('vel last', self.iBnd[0][0].V[-1,:])
print('Rho last', self.iBnd[0][0].Rho[-1]) # print('Rho last', self.iBnd[0][0].Rho[-1])
print('M last', self.iBnd[0][0].M[-1]) # print('M last', self.iBnd[0][0].M[-1])
import matplotlib # import matplotlib
matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting # matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting
from matplotlib import pyplot as plt # from matplotlib import pyplot as plt
plt.figure() # plt.figure()
plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].M, 'x--') # plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].M, 'x--')
plt.xlabel('$x$') # plt.xlabel('$x$')
plt.ylabel('Mach number') # plt.ylabel('Mach number')
plt.savefig('Mach_number.png') # Save the plot as an image file # plt.savefig('Mach_number.png') # Save the plot as an image file
print('Plot saved as Mach_number.png') # print('Plot saved as Mach_number.png')
plt.figure() # plt.figure()
plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].Rho, 'x--') # plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].Rho, 'x--')
plt.xlabel('$x$') # plt.xlabel('$x$')
plt.ylabel('Density') # plt.ylabel('Density')
plt.savefig('Density.png') # Save the plot as an image file # plt.savefig('Density.png') # Save the plot as an image file
print('Plot saved as Density.png') # print('Plot saved as Density.png')
plt.figure() # plt.figure()
plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].V[:,0], 'x--') # plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].V[:,0], 'x--')
plt.xlabel('$x$') # plt.xlabel('$x$')
plt.ylabel('Velocity X') # plt.ylabel('Velocity X')
plt.savefig('Velocity_X.png') # Save the plot as an image file # plt.savefig('Velocity_X.png') # Save the plot as an image file
print('Plot saved as Velocity_X.png') # print('Plot saved as Velocity_X.png')
plt.figure() # plt.figure()
plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].V[:,1], 'x--') # plt.plot(self.iBnd[0][0].nodesCoord[:, 0], self.iBnd[0][0].V[:,1], 'x--')
plt.xlabel('$x$') # plt.xlabel('$x$')
plt.ylabel('Velocity Y') # plt.ylabel('Velocity Y')
plt.savefig('Velocity_Y.png') # Save the plot as an image file # plt.savefig('Velocity_Y.png') # Save the plot as an image file
print('Plot saved as Velocity_Y.png') # print('Plot saved as Velocity_Y.png')
def setBlowingVelocity(self): def setBlowingVelocity(self):
""" Extract the solution of the viscous calculation (blowing velocity) """ Extract the solution of the viscous calculation (blowing velocity)
and use it as a boundary condition in the inviscid solver. and use it as a boundary condition in the inviscid solver.
""" """
print('SU2Interface::Imposing blowing velocity boundary conditions.') # print('SU2Interface::Imposing blowing velocity boundary conditions.')
# interpolate blowing velocity from elements to nodes # interpolate blowing velocity from elements to nodes
from scipy.interpolate import interp1d from scipy.interpolate import interp1d
blowingNodes = interp1d(self.iBnd[0][0].elemsCoord[:,0], self.iBnd[0][0].blowingVel, kind='linear', fill_value='extrapolate')(self.iBnd[0][0].nodesCoord[:,0]) blowingNodes = interp1d(self.iBnd[0][0].elemsCoord[:,0], self.iBnd[0][0].blowingVel, kind='linear', fill_value='extrapolate')(self.iBnd[0][0].nodesCoord[:,0])
blowingNodes[abs(blowingNodes) > 0.5] = 1e-6
#Plot blowing velocity #Plot blowing velocity
import matplotlib # import matplotlib
matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting # matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting
from matplotlib import pyplot as plt # from matplotlib import pyplot as plt
plt.figure() # plt.figure()
plt.plot(self.iBnd[0][0].elemsCoord[:, 0], self.iBnd[0][0].blowingVel, 'o', label='Original') # plt.plot(self.iBnd[0][0].elemsCoord[:, 0], self.iBnd[0][0].blowingVel, 'o', label='Original')
plt.plot(self.iBnd[0][0].nodesCoord[:, 0], blowingNodes, 'x--', label='Interpolated') # plt.plot(self.iBnd[0][0].nodesCoord[:, 0], blowingNodes, 'x--', label='Interpolated')
plt.legend() # plt.legend()
plt.xlabel('$x$') # plt.xlabel('$x$')
plt.ylabel('Blowing velocity') # plt.ylabel('Blowing velocity')
plt.savefig('Blowing_velocity.png') # Save the plot as an image file # plt.savefig('Blowing_velocity.png') # Save the plot as an image file
print('Plot saved as Blowing_velocity.png') # print('Plot saved as Blowing_velocity.png')
if self.getnDim() == 2:
velComponents = ['VELOCITY_X', 'VELOCITY_Y']
elif self.getnDim() == 3:
velComponents = ['VELOCITY_X', 'VELOCITY_Y', 'VELOCITY_Z']
else:
raise RuntimeError('su2Interface::Incorrect number of dimensions.')
velIdx = np.zeros(self.getnDim(), dtype=int)
for i, velComp in enumerate(velComponents):
velIdx[i] = self.solver.GetPrimitiveIndices()[velComp]
# Get all the tags with the CHT option
for arfTag in self.wingTags: for arfTag in self.wingTags:
for ivertex in range(self.solver.GetNumberMarkerNodes(self.wingMarkersToID[arfTag])): for ivertex in range(self.solver.GetNumberMarkerNodes(self.wingMarkersToID[arfTag])):
nodeIndex = self.solver.GetMarkerNode(self.wingMarkersToID[arfTag], ivertex) nodeIndex = self.solver.GetMarkerNode(self.wingMarkersToID[arfTag], ivertex)
...@@ -258,9 +285,7 @@ class SU2Interface(SolversInterface): ...@@ -258,9 +285,7 @@ class SU2Interface(SolversInterface):
blw = np.zeros(3) blw = np.zeros(3)
for idim in range(self.getnDim()): for idim in range(self.getnDim()):
blw += normal[idim] * blowingNodes[blasterIndex] blw += normal[idim] * blowingNodes[blasterIndex]
for idim in range(self.getnDim()): self.solver.SetBlowingVelocity(nodeIndex, blw[0], blw[1], blw[2])
print('Setting blowing velocity on node', nodeIndex, 'blasterIndex', blasterIndex, blw[idim])
self.solver.Primitives().Set(int(nodeIndex), int(velIdx[idim]), blw[idim])
def getWing(self): def getWing(self):
if self.getnDim() == 2: if self.getnDim() == 2:
...@@ -321,19 +346,19 @@ class SU2Interface(SolversInterface): ...@@ -321,19 +346,19 @@ class SU2Interface(SolversInterface):
elemsCoord[i, :self.getnDim()] = (nodesCoord[i, :self.getnDim()] + nodesCoord[i+1, :self.getnDim()]) / 2 elemsCoord[i, :self.getnDim()] = (nodesCoord[i, :self.getnDim()] + nodesCoord[i+1, :self.getnDim()]) / 2
elemsCoord[i, -1] = i elemsCoord[i, -1] = i
import matplotlib # import matplotlib
matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting # matplotlib.use('Agg') # Use the Agg backend for non-interactive plotting
from matplotlib import pyplot as plt # from matplotlib import pyplot as plt
plt.figure() # plt.figure()
plt.plot(nodesCoord[:, 0], nodesCoord[:, 1], 'x--') # plt.plot(nodesCoord[:, 0], nodesCoord[:, 1], 'x--')
plt.plot(elemsCoord[:, 0], elemsCoord[:, 1], 'o') # plt.plot(elemsCoord[:, 0], elemsCoord[:, 1], 'o')
#plt.xlim([-0.001, 0.002]) # #plt.xlim([-0.001, 0.002])
#plt.ylim([-0.02, 0.02]) # #plt.ylim([-0.02, 0.02])
plt.xlabel('X Coordinate') # plt.xlabel('X Coordinate')
plt.ylabel('Y Coordinate') # plt.ylabel('Y Coordinate')
plt.title('Airfoil Nodes') # plt.title('Airfoil Nodes')
plt.savefig('airfoil_nodes.png') # Save the plot as an image file # plt.savefig('airfoil_nodes.png') # Save the plot as an image file
print('Plot saved as airfoil_nodes.png') # print('Plot saved as airfoil_nodes.png')
# Check that the airfoil has closed trailing edge # Check that the airfoil has closed trailing edge
if np.any(nodesCoord[0, [0,self.getnDim()-1]] != nodesCoord[-1, [0,self.getnDim()-1]]): if np.any(nodesCoord[0, [0,self.getnDim()-1]] != nodesCoord[-1, [0,self.getnDim()-1]]):
...@@ -355,7 +380,7 @@ class SU2Interface(SolversInterface): ...@@ -355,7 +380,7 @@ class SU2Interface(SolversInterface):
else: else:
print('No duplicated elements in airfoil mesh.') print('No duplicated elements in airfoil mesh.')
print('nNodes:', nodesCoord.shape[0], 'nElems:', elemsCoord.shape[0]) # print('nNodes:', nodesCoord.shape[0], 'nElems:', elemsCoord.shape[0])
self.iBnd[ibody][0].initStructures(nodesCoord.shape[0], elemsCoord.shape[0]) self.iBnd[ibody][0].initStructures(nodesCoord.shape[0], elemsCoord.shape[0])
self.iBnd[ibody][0].nodesCoord = nodesCoord self.iBnd[ibody][0].nodesCoord = nodesCoord
......
blast/tests/su2/blisu2.py
+ 19
− 7
View file @ ab8dfb9e
...@@ -17,27 +17,28 @@ ...@@ -17,27 +17,28 @@
# @author Paul Dechamps # @author Paul Dechamps
# @date 2022 # @date 2022 reworked 2025
# Test the vii implementation using SU2 as the inviscid solver # Test the vii implementation using SU2 as the inviscid solver
# Imports. # Imports.
from blast.blCoupler import Coupler
import blast.blUtils as vutils import blast.blUtils as vutils
from fwk.wutils import parseargs
def cfgSu2(): def cfgSu2(verb):
return { return {
'filename' : '/home/c130/lab/blaster/blast/tests/su2/config.cfg', 'filename' : '/home/c130/lab/blaster/blast/tests/su2/config.cfg',
'wingTags' : ['airfoil', 'airfoil_'], 'wingTags' : ['airfoil', 'airfoil_'],
'Verb': verb, # Verbosity level
} }
def cfgBlast(): def cfgBlast():
return { return {
'Re' : 1e7, # Freestream Reynolds number 'Re' : 1e7, # Freestream Reynolds number
'CFL0' : 1, # Inital CFL number of the calculation 'CFL0' : 1, # Inital CFL number of the calculation
'couplIter': 50, # Maximum number of iterations 'couplIter': 20, # Maximum number of iterations
'sections': {'airfoil': [0.0]}, 'sections': {'airfoil': [0.0]},
'spans': {'airfoil': 1.0}, 'spans': {'airfoil': 1.0},
'couplTol' : 1e-4, # Tolerance of the VII methodology 'couplTol' : 1e-6, # Tolerance of the VII methodology
'iterPrint': 1, # int, number of iterations between outputs 'iterPrint': 1, # int, number of iterations between outputs
'resetInv' : True, # bool, flag to reset the inviscid calculation at every iteration. 'resetInv' : True, # bool, flag to reset the inviscid calculation at every iteration.
'xtrF' : [None, 0.4], # Forced transition locations 'xtrF' : [None, 0.4], # Forced transition locations
...@@ -45,12 +46,23 @@ def cfgBlast(): ...@@ -45,12 +46,23 @@ def cfgBlast():
} }
def main(): def main():
args = parseargs()
icfg = cfgSu2() icfg = cfgSu2(args.verb)
vcfg = cfgBlast() vcfg = cfgBlast()
coupler, isol, vsol = vutils.initBlast(icfg, vcfg, iSolver='SU2', task='analysis') coupler, isol, vsol = vutils.initBlast(icfg, vcfg, iSolver='SU2', task='analysis')
coupler.run() coupler.run()
print('ok main') print('ok main')
import numpy as np
cpi = np.loadtxt('Cp_inviscid.dat')
cpCorrected = np.loadtxt('Cp_viscous.dat')
import matplotlib.pyplot as plt
import matplotlib
matplotlib.use('Agg')
plt.plot(cpCorrected[:,0], cpCorrected[:,1], lw=3)
plt.plot(cpi[:,0], cpi[:,1], '--', lw=3)
plt.gca().invert_yaxis()
plt.savefig('cp.png')
quit() quit()
# Extract solution # Extract solution
......
blast/tests/su2/config.cfg
+ 21
− 13
View file @ ab8dfb9e
...@@ -58,9 +58,10 @@ REF_AREA= 1.0 ...@@ -58,9 +58,10 @@ REF_AREA= 1.0
% Euler wall boundary marker(s) (NONE = no marker) % Euler wall boundary marker(s) (NONE = no marker)
MARKER_EULER= ( airfoil, airfoil_ ) MARKER_EULER= ( airfoil, airfoil_ )
% %
MARKER_MOVING= ( airfoil, airfoil_ )
%
SURFACE_MOVEMENT= (MOVING_WALL, MOVING_WALL) SURFACE_MOVEMENT= (MOVING_WALL, MOVING_WALL)
% %
MARKER_MOVING= ( airfoil, airfoil_ )
% Motion mach number (non-dimensional). Used for initializing a viscous flow % Motion mach number (non-dimensional). Used for initializing a viscous flow
% with the Reynolds number and for computing force coeffs. with dynamic meshes. % with the Reynolds number and for computing force coeffs. with dynamic meshes.
%MACH_MOTION= 0. %MACH_MOTION= 0.
...@@ -84,12 +85,9 @@ MARKER_MONITORING= ( airfoil, airfoil_ ) ...@@ -84,12 +85,9 @@ MARKER_MONITORING= ( airfoil, airfoil_ )
% %
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) % Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN_WANG
VENKAT_LIMITER_COEFF= 0.1
% %
% Courant-Friedrichs-Lewy condition of the finest grid % Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 1e3 CFL_NUMBER= 1e2
% %
% Adaptive CFL number (NO, YES) % Adaptive CFL number (NO, YES)
CFL_ADAPT= NO CFL_ADAPT= NO
...@@ -99,11 +97,11 @@ CFL_ADAPT= NO ...@@ -99,11 +97,11 @@ CFL_ADAPT= NO
CFL_ADAPT_PARAM= ( 0.1, 5.0, 50.0, 1e10 ) CFL_ADAPT_PARAM= ( 0.1, 5.0, 50.0, 1e10 )
% %
% Runge-Kutta alpha coefficients % Runge-Kutta alpha coefficients
%RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
% %
% Number of total iterations % Number of total iterations
ITER= 999999 ITER= 1000
%
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
% %
% Linear solver for implicit formulations (BCGSTAB, FGMRES) % Linear solver for implicit formulations (BCGSTAB, FGMRES)
...@@ -117,7 +115,7 @@ LINEAR_SOLVER_ERROR= 1E-6 ...@@ -117,7 +115,7 @@ LINEAR_SOLVER_ERROR= 1E-6
% %
% Max number of iterations of the linear solver for the implicit formulation % Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 10 LINEAR_SOLVER_ITER= 10
%
% -------------------------- MULTIGRID PARAMETERS -----------------------------% % -------------------------- MULTIGRID PARAMETERS -----------------------------%
% %
% Multi-Grid Levels (0 = no multi-grid) % Multi-Grid Levels (0 = no multi-grid)
...@@ -148,11 +146,21 @@ MG_DAMP_PROLONGATION= 1.0 ...@@ -148,11 +146,21 @@ MG_DAMP_PROLONGATION= 1.0
CONV_NUM_METHOD_FLOW= ROE CONV_NUM_METHOD_FLOW= ROE
% %
% 2nd and 4th order artificial dissipation coefficients % 2nd and 4th order artificial dissipation coefficients
%JST_SENSOR_COEFF= ( 0.01, 0.01 ) %JST_SENSOR_COEFF= ( 0.5, 0.02 )
%LAX_SENSOR_COEFF= 0.001
% %
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
MUSCL_FLOW= YES
%
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% Coefficient for the limiter
VENKAT_LIMITER_COEFF= 0.005
%
% --------------------------- CONVERGENCE PARAMETERS --------------------------% % --------------------------- CONVERGENCE PARAMETERS --------------------------%
% %
% Convergence criteria (CAUCHY, RESIDUAL) % Convergence criteria (CAUCHY, RESIDUAL)
...@@ -172,11 +180,11 @@ CONV_CAUCHY_EPS= 1E-10 ...@@ -172,11 +180,11 @@ CONV_CAUCHY_EPS= 1E-10
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
% %
SCREEN_WRT_FREQ_INNER= 5 SCREEN_WRT_FREQ_INNER= 200
VOLUME_OUTPUT = SOLUTION, PRIMITIVE, RMS_DENSITY VOLUME_OUTPUT = SOLUTION, PRIMITIVE, RMS_DENSITY
% Mesh input file % Mesh input file
MESH_FILENAME= /home/c130/lab/blaster/blast/models/su2/n0012_su2.su2 MESH_FILENAME= /home/c130/lab/blaster/blast/models/su2/n0012_su2_2.su2
% %
% Mesh input file format (SU2, CGNS, NETCDF_ASCII) % Mesh input file format (SU2, CGNS, NETCDF_ASCII)
MESH_FORMAT= SU2 MESH_FORMAT= SU2
......
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