Remove semi AnalysisSurfaceIntegral

trixi-framework · Sep 9, 2024 · f1fae82 · f1fae82
1 parent f9c9107
commit f1fae82
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Showing 4 changed files with 9 additions and 11 deletions.
diff --git a/examples/p4est_2d_dgsem/elixir_euler_NACA0012airfoil_mach085.jl b/examples/p4est_2d_dgsem/elixir_euler_NACA0012airfoil_mach085.jl
@@ -85,11 +85,11 @@ analysis_interval = 2000
 l_inf = 1.0 # Length of airfoil
 
 force_boundary_names = (:AirfoilBottom, :AirfoilTop)
-drag_coefficient = AnalysisSurfaceIntegral(semi, force_boundary_names,
+drag_coefficient = AnalysisSurfaceIntegral(force_boundary_names,
                                            DragCoefficientPressure(aoa(), rho_inf(),
                                                                    u_inf(equations), l_inf))
 
-lift_coefficient = AnalysisSurfaceIntegral(semi, force_boundary_names,
+lift_coefficient = AnalysisSurfaceIntegral(force_boundary_names,
                                            LiftCoefficientPressure(aoa(), rho_inf(),
                                                                    u_inf(equations), l_inf))
 

diff --git a/examples/p4est_2d_dgsem/elixir_euler_subsonic_cylinder.jl b/examples/p4est_2d_dgsem/elixir_euler_subsonic_cylinder.jl
@@ -89,11 +89,11 @@ rho_inf = 1.4
 u_inf = 0.38
 l_inf = 1.0 # Diameter of circle
 
-drag_coefficient = AnalysisSurfaceIntegral(semi, (:x_neg,),
+drag_coefficient = AnalysisSurfaceIntegral((:x_neg,),
                                            DragCoefficientPressure(aoa, rho_inf, u_inf,
                                                                    l_inf))
 
-lift_coefficient = AnalysisSurfaceIntegral(semi, (:x_neg,),
+lift_coefficient = AnalysisSurfaceIntegral((:x_neg,),
                                            LiftCoefficientPressure(aoa, rho_inf, u_inf,
                                                                    l_inf))
 

diff --git a/examples/p4est_2d_dgsem/elixir_navierstokes_NACA0012airfoil_mach08.jl b/examples/p4est_2d_dgsem/elixir_navierstokes_NACA0012airfoil_mach08.jl
@@ -120,23 +120,23 @@ summary_callback = SummaryCallback()
 analysis_interval = 2000
 
 force_boundary_names = (:AirfoilBottom, :AirfoilTop)
-drag_coefficient = AnalysisSurfaceIntegral(semi, force_boundary_names,
+drag_coefficient = AnalysisSurfaceIntegral(force_boundary_names,
                                            DragCoefficientPressure(aoa(), rho_inf(),
                                                                    u_inf(equations),
                                                                    l_inf()))
 
-lift_coefficient = AnalysisSurfaceIntegral(semi, force_boundary_names,
+lift_coefficient = AnalysisSurfaceIntegral(force_boundary_names,
                                            LiftCoefficientPressure(aoa(), rho_inf(),
                                                                    u_inf(equations),
                                                                    l_inf()))
 
-drag_coefficient_shear_force = AnalysisSurfaceIntegral(semi, force_boundary_names,
+drag_coefficient_shear_force = AnalysisSurfaceIntegral(force_boundary_names,
                                                        DragCoefficientShearStress(aoa(),
                                                                                   rho_inf(),
                                                                                   u_inf(equations),
                                                                                   l_inf()))
 
-lift_coefficient_shear_force = AnalysisSurfaceIntegral(semi, force_boundary_names,
+lift_coefficient_shear_force = AnalysisSurfaceIntegral(force_boundary_names,
                                                        LiftCoefficientShearStress(aoa(),
                                                                                   rho_inf(),
                                                                                   u_inf(equations),

diff --git a/src/callbacks_step/analysis_surface_integral_2d.jl b/src/callbacks_step/analysis_surface_integral_2d.jl
@@ -20,7 +20,6 @@ For instance, this can be used to compute the lift [`LiftCoefficientPressure`](@
 drag coefficient [`DragCoefficientPressure`](@ref) of e.g. an airfoil with the boundary
 name `:Airfoil` in 2D.
 
-- `semi::Semidiscretization`: Passed in to retrieve boundary condition information
 - `boundary_symbols::NTuple{NBoundaries, Symbol}`: Name(s) of the boundary/boundaries
   where the quantity of interest is computed
 - `variable::Variable`: Quantity of interest, like lift or drag
@@ -29,8 +28,7 @@ struct AnalysisSurfaceIntegral{Variable, NBoundaries}
     variable::Variable # Quantity of interest, like lift or drag
     boundary_symbols::NTuple{NBoundaries, Symbol} # Name(s) of the boundary/boundaries
 
-    function AnalysisSurfaceIntegral(semi,
-                                     boundary_symbols::NTuple{NBoundaries, Symbol},
+    function AnalysisSurfaceIntegral(boundary_symbols::NTuple{NBoundaries, Symbol},
                                      variable) where {NBoundaries}
         return new{typeof(variable), NBoundaries}(variable, boundary_symbols)
     end