mesh settings for gmsh changed

Author: GBenedett

ceasiompy/CPACS2GMSH/__specs__.py

@@ -156,6 +156,67 @@
     gui_group="Euler options",
 )
 
+cpacs_inout.add_input(
+    var_name="n_power_factor",
+    var_type=float,
+    default_value=2,
+    unit="1",
+    descr="Value that changes the number of cells near the aircraft parts",
+    xpath=GMSH_N_POWER_FACTOR_XPATH,
+    gui=True,
+    gui_name="n power factor",
+    gui_group="Advanced Euler mesh parameters",
+)
+
+cpacs_inout.add_input(
+    var_name="n_power_field",
+    var_type=float,
+    default_value=0.9,
+    unit="1",
+    descr="Value that changes the measure of fist cells near aircraft parts",
+    xpath=GMSH_N_POWER_FIELD_XPATH,
+    gui=True,
+    gui_name="n power field",
+    gui_group="Advanced Euler mesh parameters",
+)
+
+cpacs_inout.add_input(
+    var_name="refine_factor",
+    var_type=float,
+    default_value=2.0,
+    unit="1",
+    descr="Refinement factor of wing leading/trailing edge mesh",
+    xpath=GMSH_REFINE_FACTOR_XPATH,
+    gui=True,
+    gui_name="LE/TE refinement factor",
+    gui_group="Advanced Euler mesh parameters",
+)
+
+cpacs_inout.add_input(
+    var_name="refine_truncated",
+    var_type=bool,
+    default_value=False,
+    unit="1",
+    descr="Enable the refinement of truncated trailing edge",
+    xpath=GMSH_REFINE_TRUNCATED_XPATH,
+    gui=True,
+    gui_name="Refine truncated TE",
+    gui_group="Advanced Euler mesh parameters",
+)
+
+cpacs_inout.add_input(
+    var_name="auto_refine",
+    var_type=bool,
+    default_value=False,
+    unit="1",
+    descr="Automatically refine the mesh on surfaces that are small compare to the chosen mesh"
+    "size, this option increase the mesh generation time",
+    xpath=GMSH_AUTO_REFINE_XPATH,
+    gui=True,
+    gui_name="Auto refine",
+    gui_group="Advanced Euler mesh parameters",
+)
+
 cpacs_inout.add_input(
     var_name="n_layer",
     var_type=int,
@@ -252,66 +313,6 @@
     gui_group="General options",
 )
 
-cpacs_inout.add_input(
-    var_name="n_power_factor",
-    var_type=float,
-    default_value=2,
-    unit="1",
-    descr="Value that changes the number of cells near the aircraft parts",
-    xpath=GMSH_N_POWER_FACTOR_XPATH,
-    gui=True,
-    gui_name="n power factor",
-    gui_group="Advanced Euler mesh parameters",
-)
-
-cpacs_inout.add_input(
-    var_name="n_power_field",
-    var_type=float,
-    default_value=0.9,
-    unit="1",
-    descr="Value that changes the measure of fist cells near aircraft parts",
-    xpath=GMSH_N_POWER_FIELD_XPATH,
-    gui=True,
-    gui_name="n power field",
-    gui_group="Advanced Euler mesh parameters",
-)
-
-cpacs_inout.add_input(
-    var_name="refine_factor",
-    var_type=float,
-    default_value=2.0,
-    unit="1",
-    descr="Refinement factor of wing leading/trailing edge mesh",
-    xpath=GMSH_REFINE_FACTOR_XPATH,
-    gui=True,
-    gui_name="LE/TE refinement factor",
-    gui_group="Advanced Euler mesh parameters",
-)
-cpacs_inout.add_input(
-    var_name="refine_truncated",
-    var_type=bool,
-    default_value=False,
-    unit="1",
-    descr="Enable the refinement of truncated trailing edge",
-    xpath=GMSH_REFINE_TRUNCATED_XPATH,
-    gui=True,
-    gui_name="Refine truncated TE",
-    gui_group="Advanced Euler mesh parameters",
-)
-
-cpacs_inout.add_input(
-    var_name="auto_refine",
-    var_type=bool,
-    default_value=False,
-    unit="1",
-    descr="Automatically refine the mesh on surfaces that are small compare to the chosen mesh"
-    "size, this option increase the mesh generation time",
-    xpath=GMSH_AUTO_REFINE_XPATH,
-    gui=True,
-    gui_name="Auto refine",
-    gui_group="Advanced Euler mesh parameters",
-)
-
 cpacs_inout.add_input(
     var_name="intake_percent",
     var_type=float,

ceasiompy/CPACS2GMSH/func/generategmesh.py

@@ -931,14 +931,14 @@ def generate_gmsh(
     # the size of the points on boundaries.
 
     fuselage_maxlen, fuselage_minlen = fuselage_size(cpacs_path)
-    mesh_size_fuselage = fuselage_mesh_size_factor * fuselage_minlen
+    mesh_size_fuselage = ((fuselage_maxlen + fuselage_minlen) / 2) / fuselage_mesh_size_factor
     log.info(f"Mesh size fuselage={mesh_size_fuselage:.3f} m")
 
     create_branch(cpacs.tixi, GMSH_MESH_SIZE_FUSELAGE_XPATH)
     cpacs.tixi.updateDoubleElement(GMSH_MESH_SIZE_FUSELAGE_XPATH, mesh_size_fuselage, "%.3f")
 
     wing_maxlen, wing_minlen = wings_size(cpacs_path)
-    mesh_size_wing = wing_mesh_size_factor * wing_minlen
+    mesh_size_wing = ((wing_maxlen * 0.8 + wing_minlen) / 2) / wing_mesh_size_factor
     log.info(f"Mesh size wing={mesh_size_wing:.3f} m")
 
     create_branch(cpacs.tixi, GMSH_MESH_SIZE_WINGS_XPATH)