# RCAIDE/Framework/External_Interfaces/OpenVSP/run_vsp_mesh.py
#
# Created: Aug 2025, W. Zheng
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
try:
import vsp as vsp
except ImportError:
try:
import openvsp as vsp
except ImportError:
# This allows RCAIDE to build without OpenVSP
pass
import fileinput
from RCAIDE.Framework.External_Interfaces.OpenVSP.write_vsp_mesh import set_sources
# ----------------------------------------------------------------------------------------------------------------------
# run_vsp_mesh
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def run_vsp_mesh(geom,vsp_file, minedge,maxedge, sym=False,
farfield_scale= 2.0, farfield= False,source=False):
if sym:
f = fileinput.input(vsp_file,inplace=1)
for line in f:
if 'SymmetrySplitting' in line:
print(line[0:34] + '1' + line[35:-1])
else:
print(line)
vsp.ClearVSPModel()
vsp.ReadVSPFile(vsp_file)
#Add in a function to modify all wing-like geometry and BOR to finite trailing edge
geom_ids = vsp.FindGeoms()
for geom_id in geom_ids:
geom_type = vsp.GetGeomTypeName(geom_id)
if geom_type in ["Wing"]:
geom_name = vsp.GetGeomName(geom_id)
print(f"Processing {geom_name} ({geom_type})")
subsurf_ids = vsp.GetSubSurfIDVec(geom_id)
for subsurf_id in subsurf_ids:
vsp.DeleteSubSurf(geom_id, subsurf_id)
print(f" Deleted subsurface {subsurf_id}")
# Get number of sections
xsecsurf_id = vsp.GetXSecSurf(geom_id, 0)
num_sections = vsp.GetNumXSec(xsecsurf_id)
# for i in range(num_sections):
# group = f"Close_{i}"
# # TE closure type (3 = SKEW_BOTH)
# te_type = vsp.GetParm(geom_id, "TE_Close_Type", group)
# vsp.SetParmVal(te_type, vsp.CLOSE_SKEWBOTH)
# #ensure relative thickness is used
# te_absrel = vsp.GetParm(geom_id, "TE_Close_AbsRel", group)
# vsp.SetParmVal(te_absrel, 0)
# # TE thickness
# te_thick = vsp.GetParm(geom_id, "TE_Close_Thick", group)
# vsp.SetParmVal(te_thick, minedge * 2)
# print(f" Applied TE closure settings to all {num_sections} sections.")
# if geom_type in ["BodyOfRevolution"]:
# geom_name = vsp.GetGeomName(geom_id)
# print(f"Processing {geom_name} ({geom_type})")
# # Get number of sections
# xsecsurf_id = vsp.GetXSecSurf(geom_id, 0)
# num_sections = vsp.GetNumXSec(xsecsurf_id)
# group = "Close"
# # TE closure type (3 = SKEW_BOTH)
# te_type = vsp.GetParm(geom_id, "TE_Close_Type", group)
# vsp.SetParmVal(te_type, vsp.CLOSE_SKEWBOTH)
# #ensure relative thickness is used
# te_absrel = vsp.GetParm(geom_id, "TE_Close_AbsRel", group)
# vsp.SetParmVal(te_absrel, 0)
# # TE thickness
# te_thick = vsp.GetParm(geom_id, "TE_Close_Thick", group)
# vsp.SetParmVal(te_thick, 0.01)
# print(f" Applied TE closure settings to all {num_sections} sections.")
vsp.Update()
print("Trailing edge settings updated for all wings and bodies of revolution.")
if source==True:
set_sources(geom)
vehicle_cont = vsp.FindContainer('Vehicle',0)
STL_multi = vsp.FindParm(vehicle_cont, 'MultiSolid', 'STLSettings')
vsp.SetParmVal(STL_multi, 1.0)
vsp.SetCFDMeshVal(vsp.CFD_MIN_EDGE_LEN, minedge )
vsp.SetCFDMeshVal( vsp.CFD_MAX_EDGE_LEN, maxedge)
vsp.SetCFDMeshVal( vsp.CFD_GROWTH_RATIO , 1.1 )
#vsp.SetCFDMeshVal(vsp.CFD_MAX_GAP, maxedge*0.01 )
vsp.SetCFDMeshVal( vsp.CFD_HALF_MESH_FLAG , sym)
vsp.SetCFDMeshVal( vsp.CFD_FAR_FIELD_FLAG , farfield)
if farfield:
vsp.SetCFDMeshVal( vsp.CFD_FAR_MAX_EDGE_LEN , farfield_scale/2)
vsp.SetCFDMeshVal( vsp.CFD_FAR_X_SCALE , farfield_scale)
vsp.SetCFDMeshVal( vsp.CFD_FAR_Y_SCALE , farfield_scale)
vsp.SetCFDMeshVal( vsp.CFD_FAR_Z_SCALE , 2*farfield_scale)
vsp.SetCFDMeshVal( vsp.CFD_INTERSECT_SUBSURFACE_FLAG , True)
vsp.SetComputationFileName(vsp.CFD_STL_FILE_NAME ,vsp_file)
vsp.Update()
vsp.ComputeCFDMesh(vsp.SET_ALL,vsp.SET_NONE,vsp.CFD_STL_TYPE)
return
