OasDiscipline

from philote_examples import OasDiscipline

Philote discipline wrapping an OpenAeroStruct VLM aerodynamic analysis. Accepts flight conditions as inputs and returns aerodynamic coefficients. The wing geometry (mesh and surface properties) is fixed at construction time.

Inherits from: philote_mdo.openmdao.OpenMdaoSubProblem

Constructor

OasDiscipline(mesh_dict=None, surface_options=None)

Parameters

Name	Type	Default	Description
mesh_dict	dict or None	See below	Dictionary passed to openaerostruct.geometry.utils.generate_mesh
surface_options	dict or None	None	Extra entries merged into the OAS surface dictionary

Default mesh configuration

When mesh_dict is None, the following default is used:

{
    "num_y": 7,
    "num_x": 2,
    "wing_type": "rect",
    "symmetry": True,
    "span": 10.0,
    "root_chord": 1.0,
}

Default surface properties

Property	Default	Description
name	"wing"	Surface name
symmetry	From mesh_dict	Use half-model with symmetry
S_ref_type	"wetted"	Reference area type
fem_model_type	"tube"	FEM model type
CL0	0.0	Baseline lift coefficient
CD0	0.0	Baseline drag coefficient
k_lam	0.05	Fraction of chord with laminar flow
t_over_c_cp	[0.15]	Thickness-to-chord ratio control points
c_max_t	0.303	Chordwise location of max thickness
with_viscous	False	Enable viscous drag estimation
with_wave	False	Enable wave drag estimation

Methods

initialize()

No-op. Required by the base class interface.

set_options(options)

No-op. This discipline has no client-configurable options.

_build_discipline()

Internal method called by the constructor. Performs all setup:

1. Generates the mesh using openaerostruct.geometry.utils.generate_mesh.
2. Builds the surface dictionary with default properties merged with surface_options.
3. Creates the OpenMDAO Group (OasAeroGroup) and adds it via self.add_group().
4. Maps inputs from the Philote interface to the internal problem.
5. Maps outputs from the internal problem to the Philote interface.

Mapped Inputs

Philote Name	OpenMDAO Path	Shape	Units
v	v	(1,)	m/s
alpha	alpha	(1,)	deg
Mach_number	Mach_number	(1,)	--
re	re	(1,)	1/m
rho	rho	(1,)	kg/m^3
cg	cg	(3,)	m

Mapped Outputs

Philote Name	OpenMDAO Path	Shape	Units
CL	aero_point_0.wing_perf.CL	(1,)	--
CD	aero_point_0.wing_perf.CD	(1,)	--
CM	aero_point_0.CM	(3,)	--

---

OasAeroGroup

from philote_examples.oas.oas_discipline import OasAeroGroup

OpenMDAO Group containing OAS Geometry + AeroPoint for one lifting surface. An IndepVarComp exposes six flow-condition variables at the group level. Explicit connections route them to AeroPoint and wire the mesh and thickness-to-chord ratio from Geometry.

Inherits from: openmdao.api.Group

Constructor

OasAeroGroup(surface=surface_dict)

The surface dictionary is passed via OpenMDAO options.

Options

Name	Type	Description
surface	dict	OAS surface dictionary (must include "name", "mesh", etc.)

Internal Components

Subsystem	Class	Description
flow_vars	IndepVarComp	Exposes v, alpha, Mach_number, re, rho, cg
{surface_name}	Geometry	Applies twist/chord/shear to the baseline mesh
aero_point_0	AeroPoint	VLM solver for a single flight condition

Internal Connections

• {name}.mesh -> aero_point_0.{name}.def_mesh
• {name}.mesh -> aero_point_0.aero_states.{name}_def_mesh
• {name}.t_over_c -> aero_point_0.{name}_perf.t_over_c
• Flow variables (v, alpha, etc.) -> aero_point_0.{var}

Example

from philote_examples import OasDiscipline
from philote_mdo.general import run_server

# Default rectangular wing
discipline = OasDiscipline()
run_server(discipline, port=50051)

# CRM wing with viscous drag
discipline = OasDiscipline(
    mesh_dict={
        "num_y": 13,
        "num_x": 3,
        "wing_type": "CRM",
        "symmetry": True,
        "num_twist_cp": 5,
    },
    surface_options={
        "with_viscous": True,
        "CD0": 0.015,
    },
)
run_server(discipline, port=50051)