Update deprecated EXT_ITER option in test configs

TestCases/euler/CRM/inv_CRM_JST.cfg

@@ -43,11 +43,11 @@ MARKER_MONITORING= ( fuselage , Wing , HTP )
 % ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
 %
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
-CFL_NUMBER= 5.0
+CFL_NUMBER= 100.0
 CFL_ADAPT= NO
 CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
 RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
-EXT_ITER= 99999
+ITER= 5000
 LINEAR_SOLVER= FGMRES
 LINEAR_SOLVER_ERROR= 1E-1
 LINEAR_SOLVER_ITER= 3
@@ -56,11 +56,12 @@ LINEAR_SOLVER_ITER= 3
 %
 MGLEVEL= 3
 MGCYCLE= V_CYCLE
-MG_PRE_SMOOTH= ( 4, 4, 4, 4 )
-MG_POST_SMOOTH= ( 4, 4, 4, 4 )
+MG_PRE_SMOOTH= ( 2, 2, 2, 2 )
+MG_POST_SMOOTH= ( 2, 2, 2, 2 )
 MG_CORRECTION_SMOOTH= ( 1, 1, 1, 1 )
-MG_DAMP_RESTRICTION= 0.5
-MG_DAMP_PROLONGATION= 0.5
+MG_DAMP_RESTRICTION= 0.75
+MG_DAMP_PROLONGATION= 0.75
+SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_MOMENTUM-Z, RMS_ENERGY)
 
 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
 %

TestCases/euler/channel/inv_channel.cfg

@@ -47,11 +47,11 @@ MARKER_MONITORING= ( upper_wall, lower_wall )
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
 %
 NUM_METHOD_GRAD= GREEN_GAUSS
-CFL_NUMBER= 6.0
+CFL_NUMBER= 30.0
 CFL_ADAPT= NO
 CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
 RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
-EXT_ITER= 999999
+ITER= 10000
 
 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
 %

TestCases/navierstokes/naca0012/lam_NACA0012.cfg

@@ -42,11 +42,11 @@ MARKER_MONITORING= ( airfoil )
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
 %
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
-CFL_NUMBER= 1.0
+CFL_NUMBER= 30.0
 CFL_ADAPT= NO
-CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
+CFL_ADAPT_PARAM= ( 0.5, 1.5, 1.0, 100.0 )
 RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
-EXT_ITER= 99999
+ITER= 10000
 LINEAR_SOLVER= FGMRES
 LINEAR_SOLVER_ERROR= 1E-1
 LINEAR_SOLVER_ITER= 3

TestCases/rans/flatplate/turb_SST_flatplate.cfg

@@ -45,11 +45,11 @@ MARKER_MONITORING= ( wall )
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
 %
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
-CFL_NUMBER= 10.0
-CFL_ADAPT= NO
-CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
+CFL_NUMBER= 50.0
+CFL_ADAPT= YES
+CFL_ADAPT_PARAM= ( 0.5, 1.2, 10.0, 200.0 )
 RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
-EXT_ITER= 99999
+ITER= 30000
 
 % ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
 %
@@ -61,6 +61,7 @@ SENS_REMOVE_SHARP= NO
 % -------------------------- MULTIGRID PARAMETERS -----------------------------%
 %
 MGLEVEL= 3
+SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, RMS_TKE, RMS_DISSIPATION)
 MGCYCLE= V_CYCLE
 MG_PRE_SMOOTH= ( 4, 4, 4, 4 )
 MG_POST_SMOOTH= ( 4, 4, 4, 4)
@@ -84,7 +85,7 @@ SLOPE_LIMITER_TURB= VENKATAKRISHNAN
 TIME_DISCRE_TURB= EULER_IMPLICIT
 
 % --------------------------- CONVERGENCE PARAMETERS --------------------------%
-CONV_RESIDUAL_MINVAL= -15
+CONV_RESIDUAL_MINVAL= -12
 CONV_STARTITER= 10
 CONV_CAUCHY_ELEMS= 100
 CONV_CAUCHY_EPS= 1E-6

TestCases/rans/s809/turb_S809.cfg

@@ -46,7 +46,8 @@ NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
 CFL_NUMBER= 10.0
 CFL_ADAPT= NO
 CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
-EXT_ITER= 99999
+SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, RMS_NU_TILDE)
+ITER= 10000
 LINEAR_SOLVER= FGMRES
 LINEAR_SOLVER_ERROR= 1E-4
 LINEAR_SOLVER_ITER= 2

TestCases/serial_regression.py

@@ -160,6 +160,22 @@ def main():
     bluntbody.test_vals = [0.666162, 7.055023, -0.000093, 3.916825]
     test_list.append(bluntbody)
 
+    # Inviscid channel with bump, subsonic
+    inv_channel           = TestCase('inv_channel')
+    inv_channel.cfg_dir   = "euler/channel"
+    inv_channel.cfg_file  = "inv_channel.cfg"
+    inv_channel.test_iter = 20
+    inv_channel.test_vals = [-2.881210, -0.363528, -0.766663, 2.541394]
+    test_list.append(inv_channel)
+
+    # CRM DPW4 wing-body, transonic
+    inv_crm_jst           = TestCase('inv_crm_jst')
+    inv_crm_jst.cfg_dir   = "euler/CRM"
+    inv_crm_jst.cfg_file  = "inv_CRM_JST.cfg"
+    inv_crm_jst.test_iter = 20
+    inv_crm_jst.test_vals = [-2.000366, -1.822591, -1.831202, -1.712343, -1.392624]
+    test_list.append(inv_crm_jst)
+
     ##########################
     ###  Compressible N-S  ###
     ##########################
@@ -212,6 +228,14 @@ def main():
     poiseuille_profile.test_vals_aarch64 = [-12.009012, -7.262299, -0.000000, 2.089953] #last 4 columns
     test_list.append(poiseuille_profile)
 
+    # Laminar NACA0012
+    lam_naca0012           = TestCase('lam_naca0012')
+    lam_naca0012.cfg_dir   = "navierstokes/naca0012"
+    lam_naca0012.cfg_file  = "lam_NACA0012.cfg"
+    lam_naca0012.test_iter = 20
+    lam_naca0012.test_vals = [-5.522140, -3.127430, -3.286926, -0.109971]
+    test_list.append(lam_naca0012)
+
     ##########################
     ### Compressible RANS  ###
     ##########################
@@ -358,6 +382,22 @@ def main():
     propeller.timeout   = 3200
     test_list.append(propeller)
 
+    # SST flat plate
+    turb_sst_flatplate           = TestCase('turb_sst_flatplate')
+    turb_sst_flatplate.cfg_dir   = "rans/flatplate"
+    turb_sst_flatplate.cfg_file  = "turb_SST_flatplate.cfg"
+    turb_sst_flatplate.test_iter = 20
+    turb_sst_flatplate.test_vals = [-4.894651, -1.648175, -2.218517, 0.580205, -0.691347, 4.979689]
+    test_list.append(turb_sst_flatplate)
+
+    # S809 wind turbine airfoil, SA
+    turb_s809           = TestCase('turb_s809')
+    turb_s809.cfg_dir   = "rans/s809"
+    turb_s809.cfg_file  = "turb_S809.cfg"
+    turb_s809.test_iter = 20
+    turb_s809.test_vals = [-4.630441, -3.675887, -3.599443, -2.233596, -10.265408]
+    test_list.append(turb_s809)
+
     #######################################
     ### Axisymmetric Compressible RANS  ###
     #######################################