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trixi-framework · Mar 29, 2024 · c156876 · c156876
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commit c156876
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diff --git a/examples/p4est_2d_dgsem/elixir_euler_NACA0012airfoil_mach085.jl b/examples/p4est_2d_dgsem/elixir_euler_NACA0012airfoil_mach085.jl
@@ -19,7 +19,7 @@ u_inf(equations) = mach_inf() * c_inf(equations)
     v1 = u_inf(equations) * cos(aoa())
     v2 = u_inf(equations) * sin(aoa())
 
-    prim = SVector(rho_inf(), v1, v2, pre_inf())
+    prim = SVector(rho_inf(), v1, v2, p_inf())
     return prim2cons(prim, equations)
 end
 
@@ -107,7 +107,7 @@ save_solution = SaveSolutionCallback(interval = 500,
                                      solution_variables = cons2prim)
 
 # Small time step should be used to reach steady state
-stepsize_callback = StepsizeCallback(cfl = 0.25)
+stepsize_callback = StepsizeCallback(cfl = 1.0)
 
 amr_indicator = IndicatorLöhner(semi, variable = Trixi.density)
 
@@ -127,7 +127,7 @@ callbacks = CallbackSet(summary_callback, analysis_callback, alive_callback, sav
 
 ###############################################################################
 # run the simulation
-sol = solve(ode, SSPRK54(),
+sol = solve(ode, SSPRK54(thread = OrdinaryDiffEq.True()),
             dt = 1.0, # solve needs some value here but it will be overwritten by the stepsize_callback
             save_everystep = false, callback = callbacks);
 summary_callback() # print the timer summary
diff --git a/src/callbacks_step/analysis_surface_integral_2d.jl b/src/callbacks_step/analysis_surface_integral_2d.jl
@@ -66,8 +66,8 @@ end
 
 Compute the lift coefficient
 ```math
-C_{L,p} \coloneqq \frac{\oint_{\partial \Omega} p \boldsymbol n \cdot \psi_L \, \mathrm{d} S}
-                        {0.5 \cdot \rho_{\infty} \cdot U_{\infty}^2 \cdot L_{\infty}}
+C_{L,p} \\coloneqq \\frac{\\oint_{\\partial \\Omega} p \\boldsymbol n \\cdot \\psi_L \\, \\mathrm{d} S}
+                        {0.5 \\cdot \\rho_{\\infty} \\cdot U_{\\infty}^2 \\cdot L_{\\infty}}
 ```
 based on the pressure distribution along a boundary.
 Supposed to be used in conjunction with [`AnalysisSurfaceIntegral`](@ref)
@@ -93,8 +93,8 @@ end
 
 Compute the drag coefficient
 ```math
-C_{D,p} \coloneqq \frac{\oint_{\partial \Omega} p \boldsymbol n \cdot \psi_D \, \mathrm{d} S}
-                        {0.5 \cdot \rho_{\infty} \cdot U_{\infty}^2 \cdot L_{\infty}}
+C_{D,p} \\coloneqq \\frac{\\oint_{\\partial \\Omega} p \\boldsymbol n \\cdot \\psi_D \\, \\mathrm{d} S}
+                        {0.5 \\cdot \\rho_{\\infty} \\cdot U_{\\infty}^2 \\cdot L_{\\infty}}
 ```
 based on the pressure distribution along a boundary.
 Supposed to be used in conjunction with [`AnalysisSurfaceIntegral`](@ref)

diff --git a/test/test_p4est_2d.jl b/test/test_p4est_2d.jl
@@ -574,12 +574,12 @@ end
     @test_trixi_include(joinpath(EXAMPLES_DIR,
                                  "elixir_euler_NACA0012airfoil_mach085.jl"),
                         l2=[
-                            5.37640294704164e-7, 6.418954697992308e-6,
-                            1.0332595763357066e-5, 0.0006353813399881882,
+                            5.371568111383228e-7, 6.4158131303956445e-6,
+                            1.0324346542348325e-5, 0.0006348064933187732,
                         ],
                         linf=[
-                            0.0016284523634016628, 0.028505821812697323,
-                            0.029918806073518, 1.9505653217814127,
+                            0.0016263400091978443, 0.028471072159724428,
+                            0.02986133204785877, 1.9481060511014872,
                         ],
                         base_level=0, med_level=1, max_level=1,
                         tspan=(0.0, 0.0001),
@@ -608,8 +608,8 @@ end
     lift = Trixi.analyze(lift_coefficient, du, u, tspan[2], mesh, equations, solver,
                          semi.cache)
 
-    @test isapprox(lift, 0.026397498239816828, atol = 1e-13)
-    @test isapprox(drag, 0.10908833968266139, atol = 1e-13)
+    @test isapprox(lift, 0.0262382560809345, atol = 1e-13)
+    @test isapprox(drag, 0.10898248971932244, atol = 1e-13)
 end
 end