From 727915b87f68272cf18430a6634f8bb5e1abd874 Mon Sep 17 00:00:00 2001
From: Paul Dechamps <paul.dechamps@uliege.be>
Date: Tue, 7 Jan 2025 17:39:14 +0100
Subject: [PATCH] (refactor) Refactor RAE 3D case
---
blast/tests/dart/rae2822_3D.py | 49 ++++++++++++----------------------
1 file changed, 17 insertions(+), 32 deletions(-)
diff --git a/blast/tests/dart/rae2822_3D.py b/blast/tests/dart/rae2822_3D.py
index 61167b6..52ee476 100644
--- a/blast/tests/dart/rae2822_3D.py
+++ b/blast/tests/dart/rae2822_3D.py
@@ -18,23 +18,13 @@
# @author Paul Dechamps
# @date 2022
-# Test the blast implementation. The test case is a compressible attached transitional flow.
+# Test the blaster 3D implementation.
# Tested functionalities;
-# - Time integration.
-# - Two time-marching techniques (agressive and safe).
-# - Transition routines.
-# - Forced transition.
-# - Compressible flow routines.
-# - Laminar and turbulent flow.
-#
-# Untested functionalities.
-# - Separation routines.
-# - Multiple failure case at one iteration.
-# - Response to unconverged inviscid solver.
+# - Fully turbulent 3D compressible flow.
# Imports.
-import blast.utils as viscUtils
+import blast.utils as vutils
import numpy as np
import os.path
@@ -66,7 +56,6 @@ def cfgInviscid(nthrds, verb):
'WakeTips' : ['wakeTip'], # LIST of names of physical group containing the edge of the wake
'Tes' : ['te'], # LIST of names of physical group containing the trailing edge
'Symmetry': 'symmetry', # name of physical group containing the symmetry BC
- 'dbc' : True,
'Upstream' : 'upstream',
# Freestream
'M_inf' : 0.8, # freestream Mach number
@@ -93,24 +82,23 @@ def cfgBlast(verb):
'Minf' : 0.8, # Freestream Mach number (used for the computation of the time step only)
'CFL0' : 1, # Inital CFL number of the calculation
- 'sections' : np.linspace(0.01, 0.95, 3),
- 'writeSections': [0.2, 0.4, 0.6, 0.8, 1.0],
- 'Sym':[0.],
- 'span': 1.,
- 'interpolator': 'Rbf',
- 'rbftype': 'linear',
- 'smoothing': 1e-8,
- 'degree': 0,
- 'neighbors': 10,
- 'saveTag': 4,
+ 'sections' : np.linspace(0.01, 0.95, 3), # Sections on the wing
+ 'writeSections': [0.2, 0.4, 0.6, 0.8, 1.0], # Spanwise locations to write the solution
+ 'Sym':[0.], # Symmetry plane
+ 'span': 1., # Span of the wing
+ 'interpolator': 'Rbf', # Interpolator type
+ 'rbftype': 'linear', # Radial basis function (rbf) type
+ 'smoothing': 1e-8, # rbf smoothing factor
+ 'degree': 0, # Degree of the interpolator
+ 'neighbors': 10, # Number of neighbors for the interpolator
+ 'saveTag': 4, # Tag to save the solution with VTK
'Verb': verb, # Verbosity level of the solver
- 'couplIter': 5, # Maximum number of iterations
+ 'couplIter': 5, # Maximum number of iterations
'couplTol' : 5e-2, # Tolerance of the VII methodology
'iterPrint': 1, # int, number of iterations between outputs
'resetInv' : False, # bool, flag to reset the inviscid calculation at every iteration.
- 'xtrF' : [0., 0.], # Forced transition location
- 'nDim' : 3
+ 'xtrF' : [0., 0.], # Forced transition locations
}
def main():
@@ -127,11 +115,11 @@ def main():
'progLe': 1.1, 'progMid': 1.0, 'progTe': 1.0, 'progSpan': 1.0, 'progWake': 1.15}
vMeshFile = os.path.abspath(os.path.join(os.path.abspath(__file__), '../../../models/dart/rae_3_visc.geo'))
- vMsh = viscUtils.mesh(vMeshFile, parsViscous)
+ vMsh = vutils.mesh(vMeshFile, parsViscous)
vcfg['vMsh'] = vMsh
tms['pre'].start()
- coupler, isol, vsol = viscUtils.initBlast(icfg, vcfg)
+ coupler, isol, vsol = vutils.initBlast(icfg, vcfg)
tms['pre'].stop()
print(ccolors.ANSI_BLUE + 'PySolving...' + ccolors.ANSI_RESET)
@@ -144,9 +132,6 @@ def main():
print(' Re M alpha Cl Cd Cd_wake Cdp Cdf Cm')
print('{0:6.1f}e6 {1:8.2f} {2:8.1f} {3:8.4f} {4:8.4f} {5:8.4f} {6:8.4f} {7:8.4f} {8:8.4f}'.format(vcfg['Re']/1e6, isol.getMinf(), isol.getAoA()*180/math.pi, isol.getCl(), vsol.Cdf + isol.getCd(), vsol.Cdt, vsol.Cdp, vsol.Cdf, isol.getCm()))
- # Write results to file.
- vSolution = viscUtils.getSolution(isol.sec, write=True, toW='all')
-
# Save results
isol.save(sfx='_viscous')
tms['total'].stop()
--
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