mesh size factor from geometry evaluation

cfsengineering · Nov 20, 2023 · cac70fb · cac70fb
1 parent ac2d0b7
commit cac70fb
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Showing 5 changed files with 387 additions and 20 deletions.
diff --git a/ceasiompy/CPACS2GMSH/__specs__.py b/ceasiompy/CPACS2GMSH/__specs__.py
@@ -18,6 +18,8 @@
     GMSH_REFINE_FACTOR_XPATH,
     GMSH_SYMMETRY_XPATH,
     SU2MESH_XPATH,
+    GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
+    GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,
 )
 from ceasiompy.utils.moduleinterfaces import CPACSInOut
 
@@ -97,30 +99,55 @@
     gui_group="Mesh size",
 )
 
+# cpacs_inout.add_input(
+#     var_name="fuselage_mesh_size",
+#     var_type=float,
+#     default_value=0.3,
+#     unit="[m]",
+#     descr="Value assigned for the fuselage surfaces mesh size",
+#     xpath=GMSH_MESH_SIZE_FUSELAGE_XPATH,
+#     gui=True,
+#     gui_name="Fuselage",
+#     gui_group="Mesh size",
+# )
+
 cpacs_inout.add_input(
-    var_name="fuselage_mesh_size",
+    var_name="fuselage_mesh_size_factor",
     var_type=float,
-    default_value=0.3,
-    unit="[m]",
+    default_value=1,
+    unit="1",
     descr="Value assigned for the fuselage surfaces mesh size",
-    xpath=GMSH_MESH_SIZE_FUSELAGE_XPATH,
+    xpath=GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
     gui=True,
-    gui_name="Fuselage",
+    gui_name="Fuselage factor",
     gui_group="Mesh size",
 )
 
+# cpacs_inout.add_input(
+#     var_name="wing_mesh_size",
+#     var_type=float,
+#     default_value=0.1,
+#     unit="[m]",
+#     descr="Value assigned for the wings surfaces mesh size",
+#     xpath=GMSH_MESH_SIZE_WINGS_XPATH,
+#     gui=True,
+#     gui_name="Wings",
+#     gui_group="Mesh size",
+# )
+
 cpacs_inout.add_input(
-    var_name="wing_mesh_size",
+    var_name="wing_mesh_size_factor",
     var_type=float,
-    default_value=0.123,
-    unit="[m]",
+    default_value=1,
+    unit="1",
     descr="Value assigned for the wings surfaces mesh size",
-    xpath=GMSH_MESH_SIZE_WINGS_XPATH,
+    xpath=GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,
     gui=True,
-    gui_name="Wings",
+    gui_name="Wings factor",
     gui_group="Mesh size",
 )
 
+
 cpacs_inout.add_input(
     var_name="engine_mesh_size",
     var_type=float,
@@ -240,3 +267,19 @@
     descr="Absolute path of the SU2 mesh",
     xpath=SU2MESH_XPATH,
 )
+
+cpacs_inout.add_output(
+    var_name="fuselage_mesh_size",
+    var_type=float,
+    default_value=None,
+    descr="Value assigned for the fuselage surfaces mesh size",
+    xpath=GMSH_MESH_SIZE_FUSELAGE_XPATH,
+)
+
+cpacs_inout.add_output(
+    var_name="wing_mesh_size",
+    var_type=float,
+    default_value=None,
+    descr="Value assigned for the wings surfaces mesh size",
+    xpath=GMSH_MESH_SIZE_WINGS_XPATH,
+)
diff --git a/ceasiompy/CPACS2GMSH/cpacs2gmsh.py b/ceasiompy/CPACS2GMSH/cpacs2gmsh.py
@@ -37,8 +37,8 @@
     GMSH_N_POWER_FIELD_XPATH,
     GMSH_INTAKE_PERCENT_XPATH,
     GMSH_MESH_SIZE_FARFIELD_XPATH,
-    GMSH_MESH_SIZE_FUSELAGE_XPATH,
-    GMSH_MESH_SIZE_WINGS_XPATH,
+    GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
+    GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,
     GMSH_MESH_SIZE_ENGINES_XPATH,
     GMSH_MESH_SIZE_PROPELLERS_XPATH,
     GMSH_OPEN_GUI_XPATH,
@@ -82,8 +82,8 @@ def cpacs2gmsh(cpacs_path, cpacs_out_path):
     mesh_size_farfield = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FARFIELD_XPATH, 25)
     n_power_factor = get_value_or_default(cpacs.tixi, GMSH_N_POWER_FACTOR_XPATH, 2)
     n_power_field = get_value_or_default(cpacs.tixi, GMSH_N_POWER_FIELD_XPATH, 0.9)
-    mesh_size_fuselage = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FUSELAGE_XPATH, 0.4)
-    mesh_size_wings = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_WINGS_XPATH, 0.23)
+    fuselage_mesh_size_factor = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,1)
+    wing_mesh_size_factor = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,1)
     mesh_size_engines = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_ENGINES_XPATH, 0.23)
     mesh_size_propellers = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_PROPELLERS_XPATH, 0.23)
     refine_factor = get_value_or_default(cpacs.tixi, GMSH_REFINE_FACTOR_XPATH, 7.0)
@@ -96,6 +96,7 @@ def cpacs2gmsh(cpacs_path, cpacs_out_path):
     export_brep(cpacs, brep_dir, (intake_percent, exhaust_percent))
     mesh_path, _ = generate_gmsh(
         cpacs,
+        cpacs_path,
         brep_dir,
         results_dir,
         open_gmsh=open_gmsh,
@@ -104,8 +105,8 @@ def cpacs2gmsh(cpacs_path, cpacs_out_path):
         mesh_size_farfield=mesh_size_farfield,
         n_power_factor=n_power_factor,
         n_power_field=n_power_field,
-        mesh_size_fuselage=mesh_size_fuselage,
-        mesh_size_wings=mesh_size_wings,
+        fuselage_mesh_size_factor=fuselage_mesh_size_factor,
+        wing_mesh_size_factor=wing_mesh_size_factor,
         mesh_size_engines=mesh_size_engines,
         mesh_size_propellers=mesh_size_propellers,
         refine_factor=refine_factor,

diff --git a/ceasiompy/CPACS2GMSH/func/generategmesh.py b/ceasiompy/CPACS2GMSH/func/generategmesh.py
@@ -55,6 +55,8 @@
 from ceasiompy.utils.ceasiomlogger import get_logger
 from ceasiompy.utils.ceasiompyutils import get_part_type
 
+from ceasiompy.CPACS2GMSH.func.mesh_sizing import fuselage_size, wings_size
+
 log = get_logger()
 
 
@@ -557,6 +559,7 @@ def control_disk_actuator_normal():
 
 def generate_gmsh(
     cpacs,
+    cpacs_path,
     brep_dir,
     results_dir,
     open_gmsh=False,
@@ -565,8 +568,8 @@ def generate_gmsh(
     mesh_size_farfield=25,
     n_power_factor=2,
     n_power_field=0.9,
-    mesh_size_fuselage=0.4,
-    mesh_size_wings=0.23,
+    fuselage_mesh_size_factor=1,
+    wing_mesh_size_factor=1,
     mesh_size_engines=0.23,
     mesh_size_propellers=0.23,
     refine_factor=7.0,
@@ -924,13 +927,23 @@ def generate_gmsh(
     # Thus be sure to define mesh size in a certain order to control
     # the size of the points on boundaries.
 
+    fuselage_maxlen, fuselage_minlen = fuselage_size(cpacs_path)
+    log.info(f"fuselage_minlen={fuselage_minlen}")
+    mesh_size_fuselage = fuselage_mesh_size_factor * fuselage_minlen
+    log.info(f"mesh_size_fuselage={mesh_size_fuselage}")
+
+    wing_maxlen, wing_minlen = wings_size(cpacs_path)
+    log.info(f"wing_minlen={wing_minlen}")
+    mesh_size_wing = wing_mesh_size_factor * wing_minlen
+    log.info(f"mesh_size_wing={mesh_size_wing}")    
+
     for part in aircraft_parts:
         if part.part_type == "fuselage":
             part.mesh_size = mesh_size_fuselage
             gmsh.model.mesh.setSize(part.points, part.mesh_size)
             gmsh.model.setColor(part.surfaces, *MESH_COLORS[part.part_type], recursive=False)
         elif part.part_type in ["wing", "pylon"]:
-            part.mesh_size = mesh_size_wings
+            part.mesh_size = mesh_size_wing
             gmsh.model.mesh.setSize(part.points, part.mesh_size)
             gmsh.model.setColor(part.surfaces, *MESH_COLORS[part.part_type], recursive=False)
         elif part.part_type == "engine":
@@ -967,7 +980,7 @@ def generate_gmsh(
                     final_domain.volume_tag,
                     aircraft,
                     part,
-                    mesh_size_wings,
+                    mesh_size_wing,
                     refine=refine_factor,
                     refine_truncated=refine_truncated,
                 )