Modify wrong config files and update golden for some regression cases

sdhzhs · Feb 4, 2023 · b36a7d5 · b36a7d5
1 parent 73cf011
commit b36a7d5
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Showing 7 changed files with 621 additions and 621 deletions.
diff --git a/golden/GA_W-1_cpt/Wallsol.dat b/golden/GA_W-1_cpt/Wallsol.dat
diff --git a/golden/GA_W-1_xyz/Aeroreport.dat b/golden/GA_W-1_xyz/Aeroreport.dat
@@ -18,9 +18,9 @@
  Reynolds number:   6299464.8818376791     
  Mach number:  0.14998745754354983     
  Angle of attack:   8.0199999999999996     
- Average Y+:   1.5639636160232464     
- Lift coefficient:   1.3886434698985266     
- Drag coefficient:   2.6060921697256913E-002
- Friction coefficient:   7.3377216853791668E-003
- Pitching moment coefficient (1/4 chord): -0.13177451996269005     
- Pressure center (unit chord):  0.34599788496627593        0.0000000000000000     
+ Average Y+:   1.5579863636600684     
+ Lift coefficient:   1.3640385649754456     
+ Drag coefficient:   1.6766657671030003E-002
+ Friction coefficient:   7.2381231995622304E-003
+ Pitching moment coefficient (1/4 chord): -0.11941174370394404     
+ Pressure center (unit chord):  0.33830851629984465        0.0000000000000000     
diff --git a/golden/GA_W-1_xyz/Wallsol.dat b/golden/GA_W-1_xyz/Wallsol.dat
diff --git a/golden/whitcomb_cpt/Aeroreport.dat b/golden/whitcomb_cpt/Aeroreport.dat
@@ -12,16 +12,16 @@
  File name for initialization: whitcomb_cpt/Autosave.dat                                       
  Momentum relaxation factor:  0.69999999999999996     
  Pressure relaxation factor:  0.29999999999999999     
- Energy relaxation factor:  0.69999999999999996     
+ Energy relaxation factor:  0.50000000000000000     
  Turbulence relaxation factor:  0.69999999999999996     
  ----------------------------------------------
  The aerodynamic parameters of this airfoil are:
  Reynolds number:   21424850.880931877     
  Mach number:  0.80000001017181221     
  Angle of attack:   4.0000000000000000     
- Average Y+:   3.0662681568784484     
- Lift coefficient:  0.57411919600444228     
- Drag coefficient:   5.3674029166819494E-002
- Friction coefficient:   3.6439821298977909E-003
- Pitching moment coefficient (1/4 chord): -0.12015798635276956     
- Pressure center (unit chord):  0.45904885780113380        0.0000000000000000     
+ Average Y+:   3.1253908775218768     
+ Lift coefficient:  0.94122005303444900     
+ Drag coefficient:   8.5175563152146874E-002
+ Friction coefficient:   4.2657224524792012E-003
+ Pitching moment coefficient (1/4 chord): -0.19549587298466839     
+ Pressure center (unit chord):  0.45689867211760038        0.0000000000000000     
diff --git a/golden/whitcomb_cpt/Wallsol.dat b/golden/whitcomb_cpt/Wallsol.dat
diff --git a/test/ransfoil.config.GA_W-1.xyz b/test/ransfoil.config.GA_W-1.xyz
@@ -55,7 +55,7 @@ Input temperature of wall(K):
 Input ambient pressure(Pa):
 276494
 Input turbulent viscosity ratio of free stream:
-50
+10
 Input wall roughness(m):
 0
 Input a directory of export files:

diff --git a/test/ransfoil.config.whitcomb.cpt.2 b/test/ransfoil.config.whitcomb.cpt.2
@@ -35,7 +35,7 @@ Input relaxation factor of velocity:
 Input relaxation factor of pressure:
 3e-1
 Input relaxation factor of temperature:
-7e-1
+5e-1
 Input relaxation factor of turbulence:
 7e-1
 Input number of grid points on whole airfoil(interpolation based on parametric spline):