Add wung fuselage test case. Minor bug fix.

flow/cases/b737.py

+#!/usr/bin/env python
+# -*- coding: utf-8 -*-
+#
+# @brief Boeign 737 (modified) configuration file for flow trim script
+# @authors Adrien Crovato
+
+def getParam():
+    p = {}
+    # Specific
+    rlems = 1.5*0.06 # root leading edge mesh size
+    rtems = 1.5*0.06 # root trailing edge mesh size
+    klems = 1.5*0.039 # kink leading edge mesh size
+    ktems = 1.5*0.039 # kink trailing edge mesh size
+    tlems = 1.5*0.014 # tip leading mesh size
+    ttems = 0.06 # tip trailing mesh size
+    fums = 0.1 # fuselage mesh size
+    fams = 4. # farfield mesh size
+    # Input/Output
+    p['File'] = '../models/b737mod.geo' # Input file containing the model
+    p['Pars'] = {'msLe0' : rlems, 'msTe0' : rtems, 'msLe1' : klems, 'msTe1' : ktems, 'msLe2' : tlems, 'msTe2' : ttems, 'msFus' : fums, 'msFar' : fams} # Parameters for input file model
+    p['Dim'] = 3 # Problem dimension
+    p['Format'] = 'vtk' # Save format (vtk or gmsh)
+    p['Slice'] = [3.5, 5.3, 10.5] # array of (y) coordinates to perform slice along the span (empty if none)
+    p['TagId'] = 5 # tag number of physical group to be sliced
+    # Markers
+    p['Fluid'] = 'field' # Name of physical group containing the fluid
+    p['Farfield'] = ['farfield', 'downstream'] # LIST of name of physical groups containing the farfield boundaries (downstream should be last element)
+    p['Symmetry'] = 'symmetry' # Name of physical group containing the symmetry boundaries
+    p['Body'] = ['wing', 'fuselage'] # LIST of name of physical groups containing the (solid) body boundary
+    p['Wake'] = 'wake' # Name of physical group containing the wake
+    p['WakeTip'] = 'wakeTip' # Name of physical group containing the edge of the wake
+    p['TeTip'] = 'teTip' # Name of physical group containing the edge of the wake and the trailing edge
+    # Freestream
+    p['M_inf'] = 0.75 # Freestream Mach number
+    p['CL'] = 0.3 # Target lift coefficient
+    p['AoA'] = 0. # Freestream angle of attack (guess)
+    p['dCL'] = 10.0 # Slope of CL w.r.t AoA [1/rad] (guess)
+    # Geometry
+    p['S_ref'] = 55.0 # Reference surface length
+    p['c_ref'] = 3.8 # Reference chord length
+    p['x_ref'] = 10.15 # Reference point for moment computation (x)
+    p['y_ref'] = 1.85 # Reference point for moment computation (y)
+    p['z_ref'] = -0.5 # Reference point for moment computation (z)
+    # Numerical
+    p['NSolver'] = 'Newton' # Noninear solver type (Picard or Newton)
+    p['Rel_tol'] = 1e-6 # Relative tolerance on solver residual
+    p['Abs_tol'] = 1e-8 # Absolute tolerance on solver residual
+    p['Max_it'] = 15 # Solver maximum number of iterations
+    p['LS_tol'] = 1e-6 # Tolerance on linesearch residual
+    p['Max_it_LS'] = 10 # Linesearch maximum number of iterations
+    p['AV_thrsh'] = 1e-2 # Residual threshold below which the artificial viscosity is decreased
+    p['M_crit'] = 5. # Critical Mach number above which density is damped
+    # Thermodynamic
+    p['gamma'] = 1.4 # Specific heat ratio
+    return p
+
+def main():
+    # Arguments parser
+    import argparse
+    parser = argparse.ArgumentParser()
+    parser.add_argument("-k", help="nb of threads", type=int, default=1)
+    args, extra = parser.parse_known_args()
+
+    # Script call
+    import flow.scripts.trim as t
+    trim = t.Trim(getParam(), args.k)
+    trim.run()
+    trim.disp()
+
+if __name__ == "__main__":
+    main()
\ No newline at end of file

flow/scripts/config.py

@@ -35,7 +35,6 @@ class Config:
         # mesh the airfoil
         print ccolors.ANSI_BLUE + 'Meshing the airfoil...' + ccolors.ANSI_RESET
         self.msh = gmsh.MeshLoader(p['File'],__file__).execute(**p['Pars'])
-        self.mshWriter = Writer(self.msh)
         gmshWriter = tbox.GmshExport(self.msh)
         if p['Dim'] == 2:
             mshCrck = tbox.MshCrack(self.msh, p['Dim'])
@@ -50,6 +49,7 @@ class Config:
             mshCrck.run(gmshWriter)
         del gmshWriter
         del mshCrck
+        self.mshWriter = Writer(self.msh)
         print '\n'
 
         # initialize the problem

flow/scripts/trim.py

@@ -44,7 +44,9 @@ class Trim(Config):
             self.velInfFun.set_v(-U_inf[0], -U_inf[1], -U_inf[2])
             # run the solver
             self.tms["solver"].start()
-            self.solver.run()
+            sucess = self.solver.run()
+            if not sucess:
+                raise RuntimeError('Flow solver diverged!\n')
             self.tms["solver"].stop()
             # update slope
             if it != 0:

flow/validation/agard.py

@@ -55,7 +55,6 @@ def main():
     tms['msh'].start()
     pars = {'xL' : lgt, 'yL' : wdt, 'zL' : hgt, 'xO' : xO, 'zO' : zO, 'msLeRt' : rlems, 'msTeRt' : rtems, 'msLeTp' : tlems, 'msTeTp' : ttems, 'msF' : fms}
     msh = gmsh.MeshLoader("../models/agard445.geo",__file__).execute(**pars)
-    writer = BestWriter(msh)
     # crack the mesh
     gmshWriter = tbox.GmshExport(msh)
     mshCrck = tbox.MshCrack(msh, dim)
@@ -64,6 +63,7 @@ def main():
     mshCrck.addExcluded('wakeTip')
     mshCrck.run(gmshWriter)
     del mshCrck
+    writer = BestWriter(msh)
     tms['msh'].stop()
 
     # set the problem and add medium, initial/boundary conditions

flow/validation/onera.py

@@ -53,7 +53,6 @@ def main():
     tms['msh'].start()
     pars = {'lgt' : lgt, 'wdt' : wdt, 'hgt' : hgt, 'msLeRt' : rlems, 'msTeRt' : rtems, 'msLeTp' : tlems, 'msTeTp' : ttems, 'msF' : fms}
     msh = gmsh.MeshLoader("../models/oneraM6.geo",__file__).execute(**pars)
-    writer = BestWriter(msh)
     # crack the mesh
     gmshWriter = tbox.GmshExport(msh)
     mshCrck = tbox.MshCrack(msh, dim)
@@ -62,6 +61,7 @@ def main():
     mshCrck.addExcluded('wakeTip')
     mshCrck.run(gmshWriter)
     del mshCrck
+    writer = BestWriter(msh)
     tms['msh'].stop()
 
     # set the problem and add medium, initial/boundary conditions