diff --git a/TestCases/serial_regression.py b/TestCases/serial_regression.py
index 088dc2086ac..ed1a74ca42a 100755
--- a/TestCases/serial_regression.py
+++ b/TestCases/serial_regression.py
@@ -819,6 +819,30 @@ def main():
     unst_inc_turb_naca0015_sa.test_vals = [-3.007635, -6.879816, 1.445300, 0.419281]
     unst_inc_turb_naca0015_sa.unsteady  = True
     test_list.append(unst_inc_turb_naca0015_sa)
+    # unsteady pitching NACA64A010, RANS, SA
+    unst_pitching_naca64a010_rans           = TestCase('unst_pitching_naca64a010_rans')
+    unst_pitching_naca64a010_rans.cfg_dir   = "unsteady/pitching_naca64a010_rans"
+    unst_pitching_naca64a010_rans.cfg_file  = "turb_NACA64A010.cfg"
+    unst_pitching_naca64a010_rans.test_iter = 2
+    unst_pitching_naca64a010_rans.test_vals = [-1.299045, -3.951372, 0.010139, 0.008244]
+    unst_pitching_naca64a010_rans.unsteady  = True
+    test_list.append(unst_pitching_naca64a010_rans)
+    # unsteady pitching NACA64A010, Euler
+    unst_pitching_naca64a010_euler           = TestCase('unst_pitching_naca64a010_euler')
+    unst_pitching_naca64a010_euler.cfg_dir   = "unsteady/pitching_naca64a010_euler"
+    unst_pitching_naca64a010_euler.cfg_file  = "pitching_NACA64A010.cfg"
+    unst_pitching_naca64a010_euler.test_iter = 2
+    unst_pitching_naca64a010_euler.test_vals = [-1.186839, 4.280301, -0.038811, 0.000913]
+    unst_pitching_naca64a010_euler.unsteady  = True
+    test_list.append(unst_pitching_naca64a010_euler)
+    # unsteady plunging NACA0012, Laminar NS
+    unst_plunging_naca0012           = TestCase('unst_plunging_naca0012')
+    unst_plunging_naca0012.cfg_dir   = "unsteady/plunging_naca0012"
+    unst_plunging_naca0012.cfg_file  = "plunging_NACA0012.cfg"
+    unst_plunging_naca0012.test_iter = 2
+    unst_plunging_naca0012.test_vals = [-4.083462, 1.366757, -3.718481, -0.066605]
+    unst_plunging_naca0012.unsteady  = True
+    test_list.append(unst_plunging_naca0012)
 
     # unsteady pitching NACA0012, Euler, Deforming
     unst_deforming_naca0012           = TestCase('unst_deforming_naca0012')
diff --git a/TestCases/unsteady/pitching_naca64a010_euler/pitching_NACA64A010.cfg b/TestCases/unsteady/pitching_naca64a010_euler/pitching_NACA64A010.cfg
index 3db0541e9a8..6b1e3e7192b 100644
--- a/TestCases/unsteady/pitching_naca64a010_euler/pitching_NACA64A010.cfg
+++ b/TestCases/unsteady/pitching_naca64a010_euler/pitching_NACA64A010.cfg
@@ -14,7 +14,7 @@
 SOLVER= EULER
 KIND_TURB_MODEL= NONE
 MATH_PROBLEM= DIRECT
-RESTART_SOL= NO
+RESTART_SOL= YES
 
 % ------------------------- UNSTEADY SIMULATION -------------------------------%
 %
@@ -26,7 +26,9 @@ TIME_STEP= 0.0023555025613149587
 MAX_TIME= 0.59
 % 10 periods: 0.5888756403287397
 %
-INNER_ITER= 110
+TIME_DOMAIN= YES
+TIME_ITER= 100
+INNER_ITER= 20
 UNST_ADJOINT_ITER= 251
 
 % ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
@@ -67,16 +69,15 @@ MARKER_DESIGNING = ( airfoil )
 % ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
 %
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
-CFL_NUMBER= 10.0
+CFL_NUMBER= 200.0
 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
 
 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
 %
 LINEAR_SOLVER= FGMRES
-LINEAR_SOLVER_PREC= LU_SGS
+LINEAR_SOLVER_PREC= ILU
 LINEAR_SOLVER_ERROR= 1E-6
 LINEAR_SOLVER_ITER= 5
 
@@ -131,7 +132,7 @@ CONV_CAUCHY_EPS= 1E-6
 MESH_FILENAME= mesh_NACA64A010_inv.su2
 MESH_FORMAT= SU2
 MESH_OUT_FILENAME= mesh_out
-SOLUTION_FILENAME= restart_flow
+SOLUTION_FILENAME= solution_flow
 SOLUTION_ADJ_FILENAME= solution_adj
 TABULAR_FORMAT= CSV
 CONV_FILENAME= history
@@ -142,6 +143,7 @@ VOLUME_ADJ_FILENAME= adjoint
 GRAD_OBJFUNC_FILENAME= of_grad
 SURFACE_FILENAME= surface_flow
 SURFACE_ADJ_FILENAME= surface_adjoint
+SCREEN_OUTPUT= (TIME_ITER, INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG)
 OUTPUT_WRT_FREQ= 250
 
 % --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
@@ -149,3 +151,5 @@ OUTPUT_WRT_FREQ= 250
 OPT_OBJECTIVE= DRAG * 0.001
 OPT_CONSTRAINT= ( LIFT = 0.0 ) * 0.001; ( AREA > 0.0660957 ) * 0.001
 DEFINITION_DV= ( 30, 1.0 | airfoil | 0, 0.961538461538 ); ( 30, 1.0 | airfoil | 0, 0.923076923077 ); ( 30, 1.0 | airfoil | 0, 0.884615384615 ); ( 30, 1.0 | airfoil | 0, 0.846153846154 ); ( 30, 1.0 | airfoil | 0, 0.807692307692 ); ( 30, 1.0 | airfoil | 0, 0.769230769231 ); ( 30, 1.0 | airfoil | 0, 0.730769230769 ); ( 30, 1.0 | airfoil | 0, 0.692307692308 ); ( 30, 1.0 | airfoil | 0, 0.653846153846 ); ( 30, 1.0 | airfoil | 0, 0.615384615385 ); ( 30, 1.0 | airfoil | 0, 0.576923076923 ); ( 30, 1.0 | airfoil | 0, 0.538461538462 ); ( 30, 1.0 | airfoil | 0, 0.5 ); ( 30, 1.0 | airfoil | 0, 0.461538461538 ); ( 30, 1.0 | airfoil | 0, 0.423076923077 ); ( 30, 1.0 | airfoil | 0, 0.384615384615 ); ( 30, 1.0 | airfoil | 0, 0.346153846154 ); ( 30, 1.0 | airfoil | 0, 0.307692307692 ); ( 30, 1.0 | airfoil | 0, 0.269230769231 ); ( 30, 1.0 | airfoil | 0, 0.230769230769 ); ( 30, 1.0 | airfoil | 0, 0.192307692308 ); ( 30, 1.0 | airfoil | 0, 0.153846153846 ); ( 30, 1.0 | airfoil | 0, 0.115384615385 ); ( 30, 1.0 | airfoil | 0, 0.0769230769231 ); ( 30, 1.0 | airfoil | 0, 0.0384615384615 ); ( 30, 1.0 | airfoil | 1, 0.0384615384615 ); ( 30, 1.0 | airfoil | 1, 0.0769230769231 ); ( 30, 1.0 | airfoil | 1, 0.115384615385 ); ( 30, 1.0 | airfoil | 1, 0.153846153846 ); ( 30, 1.0 | airfoil | 1, 0.192307692308 ); ( 30, 1.0 | airfoil | 1, 0.230769230769 ); ( 30, 1.0 | airfoil | 1, 0.269230769231 ); ( 30, 1.0 | airfoil | 1, 0.307692307692 ); ( 30, 1.0 | airfoil | 1, 0.346153846154 ); ( 30, 1.0 | airfoil | 1, 0.384615384615 ); ( 30, 1.0 | airfoil | 1, 0.423076923077 ); ( 30, 1.0 | airfoil | 1, 0.461538461538 ); ( 30, 1.0 | airfoil | 1, 0.5 ); ( 30, 1.0 | airfoil | 1, 0.538461538462 ); ( 30, 1.0 | airfoil | 1, 0.576923076923 ); ( 30, 1.0 | airfoil | 1, 0.615384615385 ); ( 30, 1.0 | airfoil | 1, 0.653846153846 ); ( 30, 1.0 | airfoil | 1, 0.692307692308 ); ( 30, 1.0 | airfoil | 1, 0.730769230769 ); ( 30, 1.0 | airfoil | 1, 0.769230769231 ); ( 30, 1.0 | airfoil | 1, 0.807692307692 ); ( 30, 1.0 | airfoil | 1, 0.846153846154 ); ( 30, 1.0 | airfoil | 1, 0.884615384615 ); ( 30, 1.0 | airfoil | 1, 0.923076923077 ); ( 30, 1.0 | airfoil | 1, 0.961538461538 )
+READ_BINARY_RESTART= NO
+RESTART_ITER= 2
diff --git a/TestCases/unsteady/pitching_naca64a010_rans/turb_NACA64A010.cfg b/TestCases/unsteady/pitching_naca64a010_rans/turb_NACA64A010.cfg
index ae230679efd..8a4e536d4eb 100644
--- a/TestCases/unsteady/pitching_naca64a010_rans/turb_NACA64A010.cfg
+++ b/TestCases/unsteady/pitching_naca64a010_rans/turb_NACA64A010.cfg
@@ -11,10 +11,10 @@
 
 % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
 %
-SOLVER= NAVIER_STOKES
+SOLVER= RANS
 KIND_TURB_MODEL= SA
 MATH_PROBLEM= DIRECT
-RESTART_SOL= NO
+RESTART_SOL= YES
 
 % ------------------------- UNSTEADY SIMULATION -------------------------------%
 %
@@ -27,7 +27,9 @@ TIME_STEP= 0.0023555025613149587
 MAX_TIME= 0.59
 % 10 periods: 0.5888756403287397
 %
-INNER_ITER= 2000
+TIME_DOMAIN= YES
+TIME_ITER= 100
+INNER_ITER= 30
 UNST_ADJOINT_ITER= 251
 GRID_MOVEMENT= RIGID_MOTION
 MACH_MOTION= 0.796
@@ -65,16 +67,15 @@ MARKER_DESIGNING = ( airfoil )
 % ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
 %
 NUM_METHOD_GRAD= GREEN_GAUSS
-CFL_NUMBER= 4.0
+CFL_NUMBER= 200.0
 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
 
 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
 %
 LINEAR_SOLVER= FGMRES
-LINEAR_SOLVER_PREC= LU_SGS
+LINEAR_SOLVER_PREC= ILU
 LINEAR_SOLVER_ERROR= 1E-6
 LINEAR_SOLVER_ITER= 5
 
@@ -139,7 +140,7 @@ CONV_CAUCHY_EPS= 1E-5
 MESH_FILENAME= mesh_NACA64A010_turb.su2
 MESH_FORMAT= SU2
 MESH_OUT_FILENAME= mesh_out
-SOLUTION_FILENAME= restart_flow
+SOLUTION_FILENAME= solution_flow
 SOLUTION_ADJ_FILENAME= restart_adj
 TABULAR_FORMAT= CSV
 CONV_FILENAME= history
@@ -150,6 +151,7 @@ VOLUME_ADJ_FILENAME= adjoint
 GRAD_OBJFUNC_FILENAME= of_grad
 SURFACE_FILENAME= surface_flow
 SURFACE_ADJ_FILENAME= surface_adjoint
+SCREEN_OUTPUT= (TIME_ITER, INNER_ITER, RMS_DENSITY, RMS_NU_TILDE, LIFT, DRAG)
 OUTPUT_WRT_FREQ= 1
 
 % --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
@@ -157,3 +159,5 @@ OUTPUT_WRT_FREQ= 1
 OPT_OBJECTIVE= DRAG * 0.001
 OPT_CONSTRAINT= ( AREA > 0.0661121 ) * 0.001
 DEFINITION_DV= ( 30, 1.0 | airfoil | 0, 0.961538461538 ); ( 30, 1.0 | airfoil | 0, 0.923076923077 ); ( 30, 1.0 | airfoil | 0, 0.884615384615 ); ( 30, 1.0 | airfoil | 0, 0.846153846154 ); ( 30, 1.0 | airfoil | 0, 0.807692307692 ); ( 30, 1.0 | airfoil | 0, 0.769230769231 ); ( 30, 1.0 | airfoil | 0, 0.730769230769 ); ( 30, 1.0 | airfoil | 0, 0.692307692308 ); ( 30, 1.0 | airfoil | 0, 0.653846153846 ); ( 30, 1.0 | airfoil | 0, 0.615384615385 ); ( 30, 1.0 | airfoil | 0, 0.576923076923 ); ( 30, 1.0 | airfoil | 0, 0.538461538462 ); ( 30, 1.0 | airfoil | 0, 0.5 ); ( 30, 1.0 | airfoil | 0, 0.461538461538 ); ( 30, 1.0 | airfoil | 0, 0.423076923077 ); ( 30, 1.0 | airfoil | 0, 0.384615384615 ); ( 30, 1.0 | airfoil | 0, 0.346153846154 ); ( 30, 1.0 | airfoil | 0, 0.307692307692 ); ( 30, 1.0 | airfoil | 0, 0.269230769231 ); ( 30, 1.0 | airfoil | 0, 0.230769230769 ); ( 30, 1.0 | airfoil | 0, 0.192307692308 ); ( 30, 1.0 | airfoil | 0, 0.153846153846 ); ( 30, 1.0 | airfoil | 0, 0.115384615385 ); ( 30, 1.0 | airfoil | 0, 0.0769230769231 ); ( 30, 1.0 | airfoil | 0, 0.0384615384615 ); ( 30, 1.0 | airfoil | 1, 0.0384615384615 ); ( 30, 1.0 | airfoil | 1, 0.0769230769231 ); ( 30, 1.0 | airfoil | 1, 0.115384615385 ); ( 30, 1.0 | airfoil | 1, 0.153846153846 ); ( 30, 1.0 | airfoil | 1, 0.192307692308 ); ( 30, 1.0 | airfoil | 1, 0.230769230769 ); ( 30, 1.0 | airfoil | 1, 0.269230769231 ); ( 30, 1.0 | airfoil | 1, 0.307692307692 ); ( 30, 1.0 | airfoil | 1, 0.346153846154 ); ( 30, 1.0 | airfoil | 1, 0.384615384615 ); ( 30, 1.0 | airfoil | 1, 0.423076923077 ); ( 30, 1.0 | airfoil | 1, 0.461538461538 ); ( 30, 1.0 | airfoil | 1, 0.5 ); ( 30, 1.0 | airfoil | 1, 0.538461538462 ); ( 30, 1.0 | airfoil | 1, 0.576923076923 ); ( 30, 1.0 | airfoil | 1, 0.615384615385 ); ( 30, 1.0 | airfoil | 1, 0.653846153846 ); ( 30, 1.0 | airfoil | 1, 0.692307692308 ); ( 30, 1.0 | airfoil | 1, 0.730769230769 ); ( 30, 1.0 | airfoil | 1, 0.769230769231 ); ( 30, 1.0 | airfoil | 1, 0.807692307692 ); ( 30, 1.0 | airfoil | 1, 0.846153846154 ); ( 30, 1.0 | airfoil | 1, 0.884615384615 ); ( 30, 1.0 | airfoil | 1, 0.923076923077 ); ( 30, 1.0 | airfoil | 1, 0.961538461538 )
+READ_BINARY_RESTART= NO
+RESTART_ITER= 2
diff --git a/TestCases/unsteady/plunging_naca0012/plunging_NACA0012.cfg b/TestCases/unsteady/plunging_naca0012/plunging_NACA0012.cfg
index 6e4bc39ea5d..b1ce80b506f 100644
--- a/TestCases/unsteady/plunging_naca0012/plunging_NACA0012.cfg
+++ b/TestCases/unsteady/plunging_naca0012/plunging_NACA0012.cfg
@@ -14,19 +14,21 @@
 SOLVER= NAVIER_STOKES
 KIND_TURB_MODEL= NONE
 MATH_PROBLEM= DIRECT
-RESTART_SOL= NO
+RESTART_SOL= YES
 
 % ------------------------- UNSTEADY SIMULATION -------------------------------%
 %
 TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
 TIME_STEP= 0.0023555025613149587
+TIME_DOMAIN= YES
+TIME_ITER= 100
 % 24 steps per period: 0.0024536485013697488
 % 25 steps per period: 0.0023555025613149587
 %
 MAX_TIME= 0.5888756403287397
 % 10 periods: 0.5888756403287397
 %
-INNER_ITER= 1000
+INNER_ITER= 50
 
 % ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
 %
@@ -62,7 +64,6 @@ CFL_NUMBER= 1.0
 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
 
 % ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
 %
@@ -118,4 +119,7 @@ VOLUME_ADJ_FILENAME= adjoint
 GRAD_OBJFUNC_FILENAME= of_grad
 SURFACE_FILENAME= surface_flow
 SURFACE_ADJ_FILENAME= surface_adjoint
+SCREEN_OUTPUT= (TIME_ITER, INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG)
 OUTPUT_WRT_FREQ= 1
+READ_BINARY_RESTART= NO
+RESTART_ITER= 2