Merge branch 'su2interface' into dev

Added SU2 interface for Harrier 8.0.1.

blast/blUtils.py

@@ -89,6 +89,8 @@ def initBlast(iconfig, vconfig, iSolver='DART', task='analysis'):
     # Inviscid solver
     if iSolver == 'DART':
         from blast.interfaces.dart.blDartInterface import DartInterface as interface
+    elif iSolver == 'SU2':
+        from blast.interfaces.su2.blSU2Interface import SU2Interface as interface
     else:
         raise RuntimeError(f"Solver {iSolver} currently not implemented")
     

blast/models/su2/n0012_su2.geo

+/* Airfoil NACA0012 */
+// This file was generated automatically using geoFoils v1.0 (https://github.com/Paul-Dech/geoFoils)
+// @date: 2025-01-07 15:28:07
+// @author: Paul Dechamps
+
+// Geometry
+DefineConstant[ xLgt = { 5.0, Name "Domain length (x-dir)" }  ];
+DefineConstant[ yLgt = { 5.0, Name "Domain length (y-dir)" }  ];
+
+// Mesh
+DefineConstant[ growthRatio = { 1.5, Name "Growth Ratio" }  ];
+DefineConstant[ msTe = { 0.01, Name "Airfoil TE mesh size" }  ];
+DefineConstant[ msLe = { 0.01, Name "Airfoil LE mesh size" }  ];
+
+// Rotation
+DefineConstant[ xRot = { 0.25, Name "Center of rotation" }  ];
+DefineConstant[ angle = { 0*Pi/180, Name "Angle of rotation" }  ];
+Geometry.AutoCoherence = 0; // Needed so that gmsh does not remove duplicate
+
+If (growthRatio == 1.0)
+   msF = msLe;
+Else
+   n = Log(1 - (1 - growthRatio) * xLgt / msLe) / Log(growthRatio);
+   msF = msLe * growthRatio^(n - 1);
+EndIf
+
+/**************
+ Geometry
+ **************/
+Te = 1; // trailing edge
+Le = 151; // leading edge
+
+Point( 1 ) = { 1.0, -0.0, 0.0, msTe };
+Point( 2 ) = { 0.99989034173742, 1.566142976e-05, 0.0};
+Point( 3 ) = { 0.99956141504943, 6.262613794e-05, 0.0};
+Point( 4 ) = { 0.99901336421414, 0.00014083544147, 0.0};
+Point( 5 ) = { 0.99824642962475, 0.0002501917354, 0.0};
+Point( 6 ) = { 0.99726094768414, 0.00039055879171, 0.0};
+Point( 7 ) = { 0.99605735065724, 0.00056176217462, 0.0};
+Point( 8 ) = { 0.99463616648149, 0.00076358976946, 0.0};
+Point( 9 ) = { 0.99299801853525, 0.00099579242133, 0.0};
+Point( 10 ) = { 0.99114362536434, 0.00125808467902, 0.0};
+Point( 11 ) = { 0.9890738003669, 0.0015501456389, 0.0};
+Point( 12 ) = { 0.98678945143658, 0.00187161988278, 0.0};
+Point( 13 ) = { 0.98429158056432, 0.0022221185031, 0.0};
+Point( 14 ) = { 0.98158128339883, 0.00260122020822, 0.0};
+Point( 15 ) = { 0.97865974876603, 0.00300847250009, 0.0};
+Point( 16 ) = { 0.97552825814758, 0.00344339291591, 0.0};
+Point( 17 ) = { 0.97218818511874, 0.0039054703252, 0.0};
+Point( 18 ) = { 0.96864099474595, 0.00439416627328, 0.0};
+Point( 19 ) = { 0.96488824294413, 0.00490891636171, 0.0};
+Point( 20 ) = { 0.96093157579425, 0.00544913165641, 0.0};
+Point( 21 ) = { 0.9567727288213, 0.00601420011357, 0.0};
+Point( 22 ) = { 0.95241352623301, 0.00660348801398, 0.0};
+Point( 23 ) = { 0.94785588011971, 0.00721634139577, 0.0};
+Point( 24 ) = { 0.94310178961561, 0.00785208747637, 0.0};
+Point( 25 ) = { 0.93815334002193, 0.00851003605407, 0.0};
+Point( 26 ) = { 0.93301270189222, 0.00918948088016, 0.0};
+Point( 27 ) = { 0.92768213008025, 0.00988970099293, 0.0};
+Point( 28 ) = { 0.92216396275101, 0.01060996200508, 0.0};
+Point( 29 ) = { 0.91646062035505, 0.01134951733663, 0.0};
+Point( 30 ) = { 0.91057460456685, 0.01210760938604, 0.0};
+Point( 31 ) = { 0.90450849718747, 0.01288347063272, 0.0};
+Point( 32 ) = { 0.8982649590121, 0.01367632466478, 0.0};
+Point( 33 ) = { 0.89184672866292, 0.01448538712671, 0.0};
+Point( 34 ) = { 0.88525662138789, 0.01530986658219, 0.0};
+Point( 35 ) = { 0.87849752782588, 0.01614896528828, 0.0};
+Point( 36 ) = { 0.8715724127387, 0.01700187987791, 0.0};
+Point( 37 ) = { 0.86448431371071, 0.01786780194847, 0.0};
+Point( 38 ) = { 0.8572363398164, 0.01874591855516, 0.0};
+Point( 39 ) = { 0.84983167025668, 0.01963541260873, 0.0};
+Point( 40 ) = { 0.84227355296434, 0.02053546317813, 0.0};
+Point( 41 ) = { 0.83456530317943, 0.02144524569925, 0.0};
+Point( 42 ) = { 0.82671030199505, 0.02236393209232, 0.0};
+Point( 43 ) = { 0.81871199487434, 0.02329069079083, 0.0};
+Point( 44 ) = { 0.81057389013916, 0.02422468668617, 0.0};
+Point( 45 ) = { 0.80229955743119, 0.02516508099279, 0.0};
+Point( 46 ) = { 0.79389262614624, 0.02611103103947, 0.0};
+Point( 47 ) = { 0.78535678384222, 0.02706168999315, 0.0};
+Point( 48 ) = { 0.77669577462167, 0.02801620652246, 0.0};
+Point( 49 ) = { 0.7679133974895, 0.02897372440866, 0.0};
+Point( 50 ) = { 0.75901350468657, 0.02993338211239, 0.0};
+Point( 51 ) = { 0.75, 0.03089431230516, 0.0};
+Point( 52 ) = { 0.74087683705086, 0.03185564137496, 0.0};
+Point( 53 ) = { 0.73164801755993, 0.03281648891572, 0.0};
+Point( 54 ) = { 0.72231758959246, 0.03377596721082, 0.0};
+Point( 55 ) = { 0.71288964578254, 0.03473318072085, 0.0};
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+Point( 57 ) = { 0.69375779322605, 0.03663718915547, 0.0};
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+Point( 61 ) = { 0.65450849718747, 0.0403776466819, 0.0};
+Point( 62 ) = { 0.64451589847224, 0.04129317864062, 0.0};
+Point( 63 ) = { 0.63445991030763, 0.04219894816377, 0.0};
+Point( 64 ) = { 0.62434494358243, 0.04309397215141, 0.0};
+Point( 65 ) = { 0.61417543505533, 0.04397725707679, 0.0};
+Point( 66 ) = { 0.60395584540888, 0.04484779918912, 0.0};
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+Point( 75 ) = { 0.51047120994168, 0.05193920055357, 0.0};
+Point( 76 ) = { 0.5, 0.05262525200057, 0.0};
+Point( 77 ) = { 0.48952879005832, 0.05328702835989, 0.0};
+Point( 78 ) = { 0.4790621731354, 0.05392346548752, 0.0};
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+Point( 80 ) = { 0.45816107833384, 0.05511608856324, 0.0};
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+Point( 90 ) = { 0.35548410152776, 0.05920918508399, 0.0};
+Point( 91 ) = { 0.34549150281253, 0.05942431764848, 0.0};
+Point( 92 ) = { 0.33556667663071, 0.05960068878005, 0.0};
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+Point( 97 ) = { 0.28711035421746, 0.05987617485653, 0.0};
+Point( 98 ) = { 0.27768241040754, 0.05980562887012, 0.0};
+Point( 99 ) = { 0.26835198244007, 0.05969197023942, 0.0};
+Point( 100 ) = { 0.25912316294914, 0.05953477449294, 0.0};
+Point( 101 ) = { 0.25, 0.059333671875, 0.0};
+Point( 102 ) = { 0.24098649531343, 0.05908834875129, 0.0};
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+Point( 151 ) = { 0.0, 0.0, 0.0, msLe };
+Point( 152 ) = { 0.00010965826258, -0.00185715090611, 0.0};
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+Point( 243 ) = { 0.67428602366091, -0.03852117526877, 0.0};
+Point( 244 ) = { 0.68406227634234, -0.03758214954874, 0.0};
+Point( 245 ) = { 0.69375779322605, -0.03663718915547, 0.0};
+Point( 246 ) = { 0.7033683215379, -0.03568722558628, 0.0};
+Point( 247 ) = { 0.71288964578254, -0.03473318072085, 0.0};
+Point( 248 ) = { 0.72231758959246, -0.03377596721082, 0.0};
+Point( 249 ) = { 0.73164801755993, -0.03281648891572, 0.0};
+Point( 250 ) = { 0.74087683705086, -0.03185564137496, 0.0};
+Point( 251 ) = { 0.75, -0.03089431230516, 0.0};
+Point( 252 ) = { 0.75901350468657, -0.02993338211239, 0.0};
+Point( 253 ) = { 0.7679133974895, -0.02897372440866, 0.0};
+Point( 254 ) = { 0.77669577462167, -0.02801620652246, 0.0};
+Point( 255 ) = { 0.78535678384222, -0.02706168999315, 0.0};
+Point( 256 ) = { 0.79389262614624, -0.02611103103947, 0.0};
+Point( 257 ) = { 0.80229955743119, -0.02516508099279, 0.0};
+Point( 258 ) = { 0.81057389013916, -0.02422468668617, 0.0};
+Point( 259 ) = { 0.81871199487434, -0.02329069079083, 0.0};
+Point( 260 ) = { 0.82671030199505, -0.02236393209232, 0.0};
+Point( 261 ) = { 0.83456530317943, -0.02144524569925, 0.0};
+Point( 262 ) = { 0.84227355296434, -0.02053546317813, 0.0};
+Point( 263 ) = { 0.84983167025668, -0.01963541260873, 0.0};
+Point( 264 ) = { 0.8572363398164, -0.01874591855516, 0.0};
+Point( 265 ) = { 0.86448431371071, -0.01786780194847, 0.0};
+Point( 266 ) = { 0.8715724127387, -0.01700187987791, 0.0};
+Point( 267 ) = { 0.87849752782588, -0.01614896528828, 0.0};
+Point( 268 ) = { 0.88525662138789, -0.01530986658219, 0.0};
+Point( 269 ) = { 0.89184672866292, -0.01448538712671, 0.0};
+Point( 270 ) = { 0.8982649590121, -0.01367632466478, 0.0};
+Point( 271 ) = { 0.90450849718747, -0.01288347063272, 0.0};
+Point( 272 ) = { 0.91057460456685, -0.01210760938604, 0.0};
+Point( 273 ) = { 0.91646062035505, -0.01134951733663, 0.0};
+Point( 274 ) = { 0.92216396275101, -0.01060996200508, 0.0};
+Point( 275 ) = { 0.92768213008025, -0.00988970099293, 0.0};
+Point( 276 ) = { 0.93301270189222, -0.00918948088016, 0.0};
+Point( 277 ) = { 0.93815334002193, -0.00851003605407, 0.0};
+Point( 278 ) = { 0.94310178961561, -0.00785208747637, 0.0};
+Point( 279 ) = { 0.94785588011971, -0.00721634139577, 0.0};
+Point( 280 ) = { 0.95241352623301, -0.00660348801398, 0.0};
+Point( 281 ) = { 0.9567727288213, -0.00601420011357, 0.0};
+Point( 282 ) = { 0.96093157579425, -0.00544913165641, 0.0};
+Point( 283 ) = { 0.96488824294413, -0.00490891636171, 0.0};
+Point( 284 ) = { 0.96864099474595, -0.00439416627328, 0.0};
+Point( 285 ) = { 0.97218818511874, -0.0039054703252, 0.0};
+Point( 286 ) = { 0.97552825814758, -0.00344339291591, 0.0};
+Point( 287 ) = { 0.97865974876603, -0.00300847250009, 0.0};
+Point( 288 ) = { 0.98158128339883, -0.00260122020822, 0.0};
+Point( 289 ) = { 0.98429158056432, -0.0022221185031, 0.0};
+Point( 290 ) = { 0.98678945143658, -0.00187161988278, 0.0};
+Point( 291 ) = { 0.9890738003669, -0.0015501456389, 0.0};
+Point( 292 ) = { 0.99114362536434, -0.00125808467902, 0.0};
+Point( 293 ) = { 0.99299801853525, -0.00099579242133, 0.0};
+Point( 294 ) = { 0.99463616648149, -0.00076358976946, 0.0};
+Point( 295 ) = { 0.99605735065724, -0.00056176217462, 0.0};
+Point( 296 ) = { 0.99726094768414, -0.00039055879171, 0.0};
+Point( 297 ) = { 0.99824642962475, -0.0002501917354, 0.0};
+Point( 298 ) = { 0.99901336421414, -0.00014083544147, 0.0};
+Point( 299 ) = { 0.99956141504943, -6.262613794e-05, 0.0};
+Point( 300 ) = { 0.99989034173742, -1.566142976e-05, 0.0};
+// Point( 301 ) = { 1.0, 0.0, 0.0, msTe };
+
+Spline(1) = {Le:1}; // upper side
+Spline(2) = {1, 300:Le}; // lower side
+
+// Rotation
+If (angle != 0)
+   For i In {Te:N:1}
+       Rotate{{0, 0, 1}, {xRot, 0, 0}, -angle} {Point{i};}
+   EndFor
+EndIf
+
+// Farfield
+Point(10001) = {1+xLgt, 0, 0,msF};
+Point(10002) = {1+xLgt, yLgt, 0,msF};
+Point(10003) = {-xLgt, yLgt, 0,msF};
+Point(10004) = {-xLgt, 0, 0,msF};
+Point(10005) = {-xLgt,-yLgt, 0,msF};
+Point(10006) = {1+xLgt, -yLgt, 0,msF};
+
+Line(10001) = {10001, 10002};
+Line(10002) = {10002, 10003};
+Line(10003) = {10003, 10004};
+Line(10004) = {10004, 10005};
+Line(10005) = {10005, 10006};
+Line(10006) = {10006, 10001};
+
+// Front and wake
+Line(10007) = {Le, 10004};
+Line(10008) = {Te, 10001};
+
+// Internal field
+Line Loop(20001) = {10008, 10001, 10002, 10003, -10007, 1};
+Line Loop(20002) = {10007, 10004, 10005, 10006, -10008, 2};
+Plane Surface(30001) = {20001};
+Plane Surface(30002) = {20002};
+
+/************************* 
+ Mesh Options 
+ *************************/
+
+Mesh.Algorithm = 5; // Delaunay
+
+/************************* 
+ Physical Groups 
+ *************************/
+
+Physical Line("farfield") = {10003, 10004, 10002, 10005, 10001, 10006};
+Physical Line("airfoil") = {1};
+Physical Line("airfoil_") = {2};
+Physical Surface("field") = {30001, 30002};

blast/tests/su2/blisu2.py

+#!/usr/bin/env python3
+# -*- coding: utf-8 -*-
+
+# Copyright 2022 University of Liège
+#
+# Licensed under the Apache License, Version 2.0 (the "License");
+# you may not use this file except in compliance with the License.
+# You may obtain a copy of the License at
+#
+#     http://www.apache.org/licenses/LICENSE-2.0
+#
+# Unless required by applicable law or agreed to in writing, software
+# distributed under the License is distributed on an "AS IS" BASIS,
+# WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+# See the License for the specific language governing permissions and
+# limitations under the License.
+
+
+# @author Paul Dechamps
+# @date 2022 reworked 2025
+# Test the vii implementation using SU2 as the inviscid solver
+
+# Imports.
+import blast.blUtils as vutils
+from fwk.wutils import parseargs
+
+def cfgSu2(verb):
+    import os
+    return {
+    'filename' : os.path.abspath(os.path.join(os.path.split(os.path.abspath(__file__))[0], "config.cfg")),
+    'meshfile': os.path.abspath(os.path.join(os.path.split(os.path.abspath(__file__))[0], "../../models/su2/n0012_su2.su2")),
+    'wingTags' : ['airfoil', 'airfoil_'],
+    'Verb': verb,               # Verbosity level
+    }
+
+def cfgBlast():
+    return {
+    'Re' : 1e7,                 # Freestream Reynolds number
+    'CFL0' : 2,                 # Inital CFL number of the calculation
+    'couplIter': 2,            # Maximum number of iterations
+    'sections': {'airfoil': [0.0]},
+    'spans': {'airfoil': 1.0},
+    'couplTol' : 1e-4,          # Tolerance of the VII methodology
+    'iterPrint': 1,             # int, number of iterations between outputs
+    'resetInv' : True,          # bool, flag to reset the inviscid calculation at every iteration.
+    'xtrF' : [None, 0.4],       # Forced transition locations
+    'interpolator' : 'Matching',# Interpolator for the coupling
+    }
+
+def main():
+    args = parseargs()
+    icfg = cfgSu2(args.verb)
+    vcfg = cfgBlast()
+    coupler, isol, vsol = vutils.initBlast(icfg, vcfg, iSolver='SU2', task='analysis')
+    coupler.run()
+
+    import numpy as np
+    cpi = np.loadtxt('Cp_inviscid.dat')
+    cpCorrected = np.loadtxt('Cp_viscous.dat')
+    import matplotlib.pyplot as plt
+    # Clear plt
+    plt.close('all')
+    plt.figure()
+    plt.plot(cpCorrected[:,0], cpCorrected[:,1], lw=3)
+    plt.plot(cpi[:,0], cpi[:,1], '--', lw=3)
+    plt.gca().invert_yaxis()
+    plt.show()
+    #plt.savefig('cp.png')
+    quit()
+
+    # Extract solution
+
+    # Display results
+    from matplotlib import pyplot as plt
+    fig, (ax1, ax2) = plt.subplots(1, 2)
+    ax1.plot(cpCorrected[:,0], cpCorrected[:,1], lw=3)
+    ax1.plot(su2API.cp0[:,0], su2API.cp0[:,1], '--', lw=1.5, color='black')
+    ax1.invert_yaxis()
+    ax1.set_ylabel('$c_p$')
+    ax2.plot(solsu2['xoc'], solsu2['Cf'], lw=3)
+    ax2.set_ylabel('$c_f$')
+    ax2.set_xlim([0,1])
+    plt.show()
+
+    plt.plot(cpCorrected[:,0], cpCorrected[:,1], lw=3, color='darkblue')
+    plt.plot(su2API.cp0[:,0], su2API.cp0[:,1], '--', lw=3, color='black')
+    plt.xticks([0, 1])
+    plt.yticks([-1, 0, 1])
+    plt.gca().invert_yaxis()
+
+    for i, spine in enumerate(plt.gca().spines.values()):
+        if i%2 != 0:
+            spine.set_visible(False)
+    plt.show()
+
+if __name__ == "__main__":
+    main()

blast/tests/su2/config.cfg

+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: Inviscid, internal flow over a bump in a channel           %
+% Author: Thomas D. Economon                                                   %
+% Institution: Stanford University                                             %
+% Date: 2012.09.29                                                             %
+% File Version 4.0.2 "Cardinal"                                                %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
+%
+% Physical governing equations (EULER, NAVIER_STOKES, NS_PLASMA)
+%                               
+SOLVER= EULER
+%
+% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
+MATH_PROBLEM= DIRECT
+%
+% Restart solution (NO, YES)
+RESTART_SOL= NO
+
+% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
+%
+% Mach number (non-dimensional, based on the free-stream values)
+MACH_NUMBER= 0.20
+%
+% Angle of attack (degrees, only for compressible flows)
+AOA= 2.0
+%
+% Side-slip angle (degrees, only for compressible flows)
+SIDESLIP_ANGLE= 0.0
+%
+% Free-stream pressure (101325.0 N/m^2 by default)
+FREESTREAM_PRESSURE= 101300.0
+%
+% Free-stream temperature (288.15 K by default)
+FREESTREAM_TEMPERATURE= 288.0
+
+REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_ONE
+
+% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
+%
+% Reference origin for moment computation
+REF_ORIGIN_MOMENT_X = 0.25
+REF_ORIGIN_MOMENT_Y = 0.00
+REF_ORIGIN_MOMENT_Z = 0.00
+%
+% Reference length for pitching, rolling, and yawing non-dimensional moment
+REF_LENGTH= 1.0
+%
+% Reference area for force coefficients (0 implies automatic calculation)
+REF_AREA= 1.0
+
+% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
+%
+% Euler wall boundary marker(s) (NONE = no marker)
+MARKER_EULER= ( airfoil, airfoil_ )
+%
+MARKER_MOVING= ( airfoil, airfoil_ )
+%
+SURFACE_MOVEMENT= (MOVING_WALL, MOVING_WALL)
+%
+% Motion mach number (non-dimensional). Used for initializing a viscous flow
+% with the Reynolds number and for computing force coeffs. with dynamic meshes.
+%MACH_MOTION= 0.
+% Inlet boundary marker(s) (NONE = no marker) 
+% Format: ( inlet marker, total temperature, total pressure, flow_direction_x, 
+%           flow_direction_y, flow_direction_z, ... ) where flow_direction is
+%           a unit vector.
+% Default: Mach ~ 0.1
+MARKER_FAR = (farfield)
+
+% ------------------------ SURFACES IDENTIFICATION ----------------------------%
+%
+% Marker(s) of the surface to be plotted or designed
+
+MARKER_PLOTTING= ( airfoil, airfoil_ )
+%
+% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
+MARKER_MONITORING= ( airfoil, airfoil_ )
+
+% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
+%
+% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
+NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
+%
+% Courant-Friedrichs-Lewy condition of the finest grid
+CFL_NUMBER= 1e2
+%
+% Adaptive CFL number (NO, YES)
+CFL_ADAPT= NO
+%
+% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
+%                                        CFL max value )
+CFL_ADAPT_PARAM= ( 0.1, 5.0, 50.0, 1e10 )
+%
+% Runge-Kutta alpha coefficients
+RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
+%
+% Number of total iterations
+ITER= 500
+%
+% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
+%
+% Linear solver for implicit formulations (BCGSTAB, FGMRES)
+LINEAR_SOLVER= FGMRES
+%
+% Preconditioner of the Krylov linear solver (ILU, JACOBI, LINELET, LU_SGS)
+LINEAR_SOLVER_PREC= ILU
+%
+% Minimum error of the linear solver for implicit formulations
+LINEAR_SOLVER_ERROR= 1E-6
+%
+% Max number of iterations of the linear solver for the implicit formulation
+LINEAR_SOLVER_ITER= 10
+%
+% -------------------------- MULTIGRID PARAMETERS -----------------------------%
+%
+% Multi-Grid Levels (0 = no multi-grid)
+MGLEVEL= 0
+%
+% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
+MGCYCLE= W_CYCLE
+%
+% Multi-grid pre-smoothing level
+MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
+%
+% Multi-grid post-smoothing level
+MG_POST_SMOOTH= ( 0, 0, 0, 0 )
+%
+% Jacobi implicit smoothing of the correction
+MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
+%
+% Damping factor for the residual restriction
+MG_DAMP_RESTRICTION= 1.0
+%
+% Damping factor for the correction prolongation
+MG_DAMP_PROLONGATION= 1.0
+
+% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
+%
+% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
+%                              TURKEL_PREC, MSW)
+CONV_NUM_METHOD_FLOW= ROE
+%
+% 2nd and 4th order artificial dissipation coefficients
+%JST_SENSOR_COEFF= ( 0.5, 0.02 )
+%LAX_SENSOR_COEFF= 0.001
+%
+% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
+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 criteria (CAUCHY, RESIDUAL)
+CONV_FIELD= RMS_DENSITY
+%
+% Min value of the residual (log10 of the residual)
+CONV_RESIDUAL_MINVAL= -8
+%
+% Start convergence criteria at iteration number
+CONV_STARTITER= 5
+%
+% Number of elements to apply the criteria
+CONV_CAUCHY_ELEMS= 100
+%
+% Epsilon to control the series convergence
+CONV_CAUCHY_EPS= 1E-10
+
+% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+%
+SCREEN_WRT_FREQ_INNER= 50
+VOLUME_OUTPUT = SOLUTION, PRIMITIVE, RMS_DENSITY
+
+% Mesh input file
+MESH_FILENAME = path/to/mesh.su2
+%
+% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
+MESH_FORMAT= SU2
+%
+% Mesh output file
+MESH_OUT_FILENAME= mesh_out.su2
+%
+% Restart flow input file
+SOLUTION_FILENAME= solution_flow.dat
+%
+% Restart adjoint input file
+SOLUTION_ADJ_FILENAME= solution_adj.dat
+%
+% Output file format (PARAVIEW, TECPLOT, STL)
+TABULAR_FORMAT= CSV
+%
+% Output file convergence history (w/o extension) 
+CONV_FILENAME= history
+%
+% Output file restart flow
+RESTART_FILENAME= restart_flow.dat
+%
+% Output file restart adjoint
+RESTART_ADJ_FILENAME= restart_adj.dat
+%
+% Output file flow (w/o extension) variables
+VOLUME_FILENAME= flow
+%
+% Output file adjoint (w/o extension) variables
+VOLUME_ADJ_FILENAME= adjoint
+%
+% Output objective function gradient (using continuous adjoint)
+GRAD_OBJFUNC_FILENAME= of_grad.dat
+%
+% Output file surface flow coefficient (w/o extension)
+SURFACE_FILENAME= surface_flow
+%
+% Output file surface adjoint coefficient (w/o extension)
+SURFACE_ADJ_FILENAME= surface_adjoint
+%
+%