Steady VLM module¶
The ezaero.vlm.steady
module includes a Vortex Lattice Method
implementation for lifting surfaces.
References
- 1
Katz, J. et al., Low-Speed Aerodynamics, 2nd ed, Cambridge University Press, 2001: Chapter 12
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class
ezaero.vlm.steady.
FlightConditions
(ui: float = 100, aoa: float = 3.141592653589793, rho: float = 1)[source]¶ Container for the flight conditions.
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class
ezaero.vlm.steady.
MeshParameters
(m: int = 4, n: int = 16)[source]¶ Container for the wing mesh parameters.
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class
ezaero.vlm.steady.
Simulation
(wing: ezaero.vlm.steady.WingParameters, mesh: ezaero.vlm.steady.MeshParameters, flight_conditions: ezaero.vlm.steady.FlightConditions)[source]¶ Simulation runner.
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wing
¶ Wing geometry definition.
- Type
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mesh
¶ Mesh specification for the wing.
- Type
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flight_conditions
¶ Flight conditions for the simulation.
- Type
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plot_wing
(**kwargs)[source]¶ Generate 3D plot of wing panels, vortex panels, and panel control points.
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-
class
ezaero.vlm.steady.
SimulationResults
(dp: numpy.ndarray, dL: numpy.ndarray, cl: numpy.ndarray, cl_wing: float, cl_span: numpy.ndarray)[source]¶ Container for the resulting distributions from the steady VLM simulation.
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dp
¶ Distribution of pressure difference between lower and upper surfaces.
- Type
np.ndarray, shape (m, n)
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dL
¶ Lift distribution.
- Type
np.ndarray, shape (m, n)
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cl
¶ Lift coefficient distribution.
- Type
np.ndarray, shape (m, n)
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cl_span
¶ Spanwise lift coefficient distribution.
- Type
np.ndarray, shape (n, )
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