from __future__ import annotations
import sys
from tests.tools.test_tools_common import StubModel, make_module
def test_wing_airfoil_and_stability_success():
# Create mock WingGeometry class
class MockWingGeometry:
def __init__(self, **kwargs):
for k, v in kwargs.items():
setattr(self, k, v)
# Mock return types matching integration functions
def mock_wing_vlm_analysis(geometry, alpha_deg_list, mach=0.2, reynolds=None):
return [
StubModel(
alpha_deg=a,
CL=0.5,
CD=0.02,
CM=-0.05,
L_D_ratio=25.0,
span_efficiency=0.85,
)
for a in alpha_deg_list
]
def mock_airfoil_polar_analysis(name, alpha_deg_list, reynolds=1e6, mach=0.1):
return [
StubModel(alpha_deg=a, cl=0.1 * a, cd=0.01, cm=-0.05, cl_cd_ratio=10.0)
for a in alpha_deg_list
]
def mock_calculate_stability(geometry, alpha_deg=2.0, mach=0.2):
return StubModel(
CL_alpha=4.5, CM_alpha=-0.5, CL_alpha_dot=None, CM_alpha_dot=None
)
sys.modules["aerospace_mcp.integrations.aero"] = make_module(
WingGeometry=MockWingGeometry,
wing_vlm_analysis=mock_wing_vlm_analysis,
airfoil_polar_analysis=mock_airfoil_polar_analysis,
calculate_stability_derivatives=mock_calculate_stability,
AIRFOIL_DATABASE={"NACA0012": {"thickness": 0.12}},
)
from aerospace_mcp.tools.aerodynamics import (
airfoil_polar_analysis,
calculate_stability_derivatives,
get_airfoil_database,
wing_vlm_analysis,
)
assert "Aerodynamic" in wing_vlm_analysis({}, {"alpha_deg_list": [0.0, 2.0]}, {})
assert "Polar Analysis" in airfoil_polar_analysis("NACA0012")
assert "CL_alpha" in calculate_stability_derivatives({}, {})
assert "NACA0012" in get_airfoil_database()
def test_aero_import_errors():
import sys
from aerospace_mcp.tools import aerodynamics as aero_tools
sys.modules["aerospace_mcp.integrations.aero"] = make_module()
assert "not available" in aero_tools.wing_vlm_analysis({}, {}, {}).lower()
assert "not available" in aero_tools.airfoil_polar_analysis("NACA0012").lower()
assert "not available" in aero_tools.calculate_stability_derivatives({}, {}).lower()
assert "not available" in aero_tools.get_airfoil_database().lower()
def test_aero_exception_branches():
import sys
def _boom(*a, **k):
raise RuntimeError("boom")
class Bad:
pass
# Need to include WingGeometry to avoid ImportError
class MockWingGeometry:
def __init__(self, **kwargs):
for k, v in kwargs.items():
setattr(self, k, v)
sys.modules["aerospace_mcp.integrations.aero"] = make_module(
WingGeometry=MockWingGeometry,
wing_vlm_analysis=_boom,
airfoil_polar_analysis=_boom,
calculate_stability_derivatives=_boom,
AIRFOIL_DATABASE=Bad(),
)
from aerospace_mcp.tools import aerodynamics as aero_tools
assert (
"error"
in aero_tools.wing_vlm_analysis({}, {"alpha_deg_list": [0.0]}, {}).lower()
)
assert "error" in aero_tools.airfoil_polar_analysis("NACA0012").lower()
assert "error" in aero_tools.calculate_stability_derivatives({}, {}).lower()
assert "error" in aero_tools.get_airfoil_database().lower()
