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trixi-framework · Feb 10, 2024 · 1a704d6 · 1a704d6
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Showing 2 changed files with 63 additions and 65 deletions.
diff --git a/examples/p4est_2d_dgsem/elixir_euler_NACA0012airfoil_mach08.jl b/examples/p4est_2d_dgsem/elixir_euler_NACA0012airfoil_mach08.jl
@@ -12,19 +12,20 @@ equations = CompressibleEulerEquations2D(1.4)
 pre_inf() = 1.0
 rho_inf() = pre_inf() / (1.0 * 287.87) # pre_inf = 1.0,  T = 1, R = 287.87
 mach_inf() = 0.85
-aoa() = pi/180.0
-c_inf(equations) = sqrt( equations.gamma * pre_inf() / rho_inf() )
+aoa() = pi / 180.0
+c_inf(equations) = sqrt(equations.gamma * pre_inf() / rho_inf())
 U_inf(equations) = mach_inf() * c_inf(equations)
 
-@inline function initial_condition_mach085_flow(x, t, equations::CompressibleEulerEquations2D)
-   # set the freestream flow parameters
-   gasGam = equations.gamma
+@inline function initial_condition_mach085_flow(x, t,
+                                                equations::CompressibleEulerEquations2D)
+    # set the freestream flow parameters
+    gasGam = equations.gamma
 
-   v1 = U_inf(equations) * cos(aoa())
-   v2 = U_inf(equations) * sin(aoa())
+    v1 = U_inf(equations) * cos(aoa())
+    v2 = U_inf(equations) * sin(aoa())
 
-   prim = SVector(rho_inf(), v1, v2, pre_inf())
-   return prim2cons(prim, equations)
+    prim = SVector(rho_inf(), v1, v2, pre_inf())
+    return prim2cons(prim, equations)
 end
 
 initial_condition = initial_condition_mach085_flow
@@ -66,14 +67,12 @@ mesh = P4estMesh{2}(mesh_file)
     return Trixi.flux_hll(u_inner, u_boundary, normal_direction, equations)
 end
 
-
-boundary_conditions = Dict(
-   :Left => boundary_condition_subsonic_constant,
-   :Right => boundary_condition_subsonic_constant,
-   :Top => boundary_condition_subsonic_constant,
-   :Bottom => boundary_condition_subsonic_constant,
-   :AirfoilBottom => boundary_condition_slip_wall,
-   :AirfoilTop => boundary_condition_slip_wall)
+boundary_conditions = Dict(:Left => boundary_condition_subsonic_constant,
+                           :Right => boundary_condition_subsonic_constant,
+                           :Top => boundary_condition_subsonic_constant,
+                           :Bottom => boundary_condition_subsonic_constant,
+                           :AirfoilBottom => boundary_condition_slip_wall,
+                           :AirfoilTop => boundary_condition_slip_wall)
 
 semi = SemidiscretizationHyperbolic(mesh, equations, initial_condition, solver,
                                     boundary_conditions = boundary_conditions)
@@ -94,10 +93,12 @@ analysis_interval = 2000
 linf = 1.0 # Length of airfoil
 
 drag_coefficient = AnalysisSurfaceIntegral(semi, boundary_condition_slip_wall,
-                                           DragCoefficient(aoa(), rho_inf(), U_inf(equations), linf))
+                                           DragCoefficient(aoa(), rho_inf(),
+                                                           U_inf(equations), linf))
 
 lift_coefficient = AnalysisSurfaceIntegral(semi, boundary_condition_slip_wall,
-                                           LiftCoefficient(aoa(), rho_inf(), U_inf(equations), linf))
+                                           LiftCoefficient(aoa(), rho_inf(),
+                                                           U_inf(equations), linf))
 
 analysis_callback = AnalysisCallback(semi, interval = analysis_interval,
                                      output_directory = "analysis_results",
@@ -115,17 +116,17 @@ save_solution = SaveSolutionCallback(interval = 500,
 # Small time step should be used to reach steady state
 stepsize_callback = StepsizeCallback(cfl = 0.25)
 
-amr_indicator = IndicatorLöhner(semi, variable=Trixi.density)
+amr_indicator = IndicatorLöhner(semi, variable = Trixi.density)
 
 amr_controller = ControllerThreeLevel(semi, amr_indicator,
-                                      base_level=1,
-                                      med_level=3, med_threshold=0.05,
-                                      max_level=4, max_threshold=0.1)
+                                      base_level = 1,
+                                      med_level = 3, med_threshold = 0.05,
+                                      max_level = 4, max_threshold = 0.1)
 
 amr_callback = AMRCallback(semi, amr_controller,
-                           interval=100,
-                           adapt_initial_condition=true,
-                           adapt_initial_condition_only_refine=true)
+                           interval = 100,
+                           adapt_initial_condition = true,
+                           adapt_initial_condition_only_refine = true)
 
 callbacks = CallbackSet(summary_callback, analysis_callback, alive_callback, save_solution,
                         stepsize_callback, amr_callback)

diff --git a/examples/p4est_2d_dgsem/elixir_navierstokes_NACA0012airfoil_mach08.jl b/examples/p4est_2d_dgsem/elixir_navierstokes_NACA0012airfoil_mach08.jl
@@ -21,19 +21,19 @@ sw_linf() = 1.0
 sw_mach_inf() = 0.8
 sw_U_inf(equations) = sw_mach_inf() * sqrt(equations.gamma * sw_pre_inf() / sw_rho_inf())
 @inline function initial_condition_mach08_flow(x, t, equations)
-   # set the freestream flow parameters
-   gasGam = equations.gamma
-   mach_inf = sw_mach_inf()
-   aoa = sw_aoa()
-   rho_inf = sw_rho_inf()
-   pre_inf = sw_pre_inf()
-   U_inf = mach_inf * sqrt(gasGam * pre_inf / rho_inf)
-
-   v1 = U_inf * cos(aoa)
-   v2 = U_inf * sin(aoa)
-
-   prim = SVector(rho_inf, v1, v2, pre_inf)
-   return prim2cons(prim, equations)
+    # set the freestream flow parameters
+    gasGam = equations.gamma
+    mach_inf = sw_mach_inf()
+    aoa = sw_aoa()
+    rho_inf = sw_rho_inf()
+    pre_inf = sw_pre_inf()
+    U_inf = mach_inf * sqrt(gasGam * pre_inf / rho_inf)
+
+    v1 = U_inf * cos(aoa)
+    v2 = U_inf * sin(aoa)
+
+    prim = SVector(rho_inf, v1, v2, pre_inf)
+    return prim2cons(prim, equations)
 end
 
 initial_condition = initial_condition_mach08_flow
@@ -65,34 +65,32 @@ mesh = P4estMesh{2}(mesh_file, initial_refinement_level = 1)
     return Trixi.flux_hll(u_inner, u_boundary, normal_direction, equations)
 end
 
+boundary_conditions = Dict(:Left => boundary_condition_subsonic_constant,
+                           :Right => boundary_condition_subsonic_constant,
+                           :Top => boundary_condition_subsonic_constant,
+                           :Bottom => boundary_condition_subsonic_constant,
+                           :AirfoilBottom => boundary_condition_slip_wall,
+                           :AirfoilTop => boundary_condition_slip_wall)
 
-boundary_conditions = Dict(
-   :Left => boundary_condition_subsonic_constant,
-   :Right => boundary_condition_subsonic_constant,
-   :Top => boundary_condition_subsonic_constant,
-   :Bottom => boundary_condition_subsonic_constant,
-   :AirfoilBottom => boundary_condition_slip_wall,
-   :AirfoilTop => boundary_condition_slip_wall)
-
-velocity_airfoil = NoSlip(
-   (x, t, equations) -> SVector(0.0, 0.0))
+velocity_airfoil = NoSlip((x, t, equations) -> SVector(0.0, 0.0))
 
 heat_airfoil = Adiabatic((x, t, equations) -> 0.0)
 
-boundary_conditions_airfoil = BoundaryConditionNavierStokesWall(
-   velocity_airfoil, heat_airfoil)
+boundary_conditions_airfoil = BoundaryConditionNavierStokesWall(velocity_airfoil,
+                                                                heat_airfoil)
 
-velocity_bc_square = NoSlip((x, t, equations) -> initial_condition_mach08_flow(x, t, equations)[2:3])
+velocity_bc_square = NoSlip((x, t, equations) -> initial_condition_mach08_flow(x, t,
+                                                                               equations)[2:3])
 heat_bc_square = Adiabatic((x, t, equations) -> 0.0)
-boundary_condition_square = BoundaryConditionNavierStokesWall(velocity_bc_square, heat_bc_square)
+boundary_condition_square = BoundaryConditionNavierStokesWall(velocity_bc_square,
+                                                              heat_bc_square)
 
-boundary_conditions_parabolic = Dict(
-   :Left => boundary_condition_square,
-   :Right => boundary_condition_square,
-   :Top => boundary_condition_square,
-   :Bottom => boundary_condition_square,
-   :AirfoilBottom => boundary_conditions_airfoil,
-   :AirfoilTop => boundary_conditions_airfoil)
+boundary_conditions_parabolic = Dict(:Left => boundary_condition_square,
+                                     :Right => boundary_condition_square,
+                                     :Top => boundary_condition_square,
+                                     :Bottom => boundary_condition_square,
+                                     :AirfoilBottom => boundary_conditions_airfoil,
+                                     :AirfoilTop => boundary_conditions_airfoil)
 
 semi = SemidiscretizationHyperbolicParabolic(mesh, (equations, equations_parabolic),
                                              initial_condition, solver;
@@ -113,10 +111,12 @@ summary_callback = SummaryCallback()
 analysis_interval = 2000
 
 drag_coefficient = AnalysisSurfaceIntegral(semi, boundary_condition_slip_wall,
-					   DragCoefficient(sw_aoa(), sw_rho_inf(), sw_U_inf(equations), sw_linf()))
+                                           DragCoefficient(sw_aoa(), sw_rho_inf(),
+                                                           sw_U_inf(equations), sw_linf()))
 
 lift_coefficient = AnalysisSurfaceIntegral(semi, boundary_condition_slip_wall,
-					   LiftCoefficient(sw_aoa(), sw_rho_inf(), sw_U_inf(equations), sw_linf()))
+                                           LiftCoefficient(sw_aoa(), sw_rho_inf(),
+                                                           sw_U_inf(equations), sw_linf()))
 
 analysis_callback = AnalysisCallback(semi, interval = analysis_interval,
                                      output_directory = "analysis_results",
@@ -131,15 +131,12 @@ save_solution = SaveSolutionCallback(interval = 500,
                                      save_final_solution = true,
                                      solution_variables = cons2prim)
 
-
 callbacks = CallbackSet(summary_callback, analysis_callback, alive_callback, save_solution)
 
 ###############################################################################
 # run the simulation
 
-
 time_int_tol = 1e-11
 sol = solve(ode, RDPK3SpFSAL49(); abstol = time_int_tol, reltol = time_int_tol,
             ode_default_options()..., callback = callbacks)
 summary_callback() # print the timer summary
-