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OpenSourceAWE
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VortexStepMethod.jl
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plot_section_polars draws cl, cd and cm against alpha per panel, for every aero model
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#847:
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Add stability_derivatives (angle of attack, sideslip) and trim_angle, built on linearize
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Add stability_derivatives (angle of attack, sideslip) and trim_angle, built on linearize
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linearize and make_dual_shadow take a BodyAerodynamics with several wings
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linearize and make_dual_shadow take a BodyAerodynamics with several wings
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set_va! turns the body about a stored reference_point, and set_va!(body_aero, settings) applies yaw_rate
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set_va! turns the body about a stored reference_point, and set_va!(body_aero, settings) applies yaw_rate
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Build a Solver from VSMSettings or from panel and section counts, deprecate the body_aero constructors, and check the sizes in solve!
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Merge pull request #349 from OpenSourceAWE/agent/337-one-name-per-app…
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Bound and trailing vortices share one segment kernel, so the trailing core induces azimuthal velocity
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Bound and trailing vortices share one segment kernel, so the trailing core induces azimuthal velocity
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Name the apparent wind va, va_vec and va_dist everywhere except the public API
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set_va! turns the body about a stored reference_point, and set_va!(body_aero, settings) applies yaw_rate
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Add stability_derivatives (angle of attack, sideslip) and trim_angle, built on linearize
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plot_section_polars draws cl, cd and cm against alpha per panel, for every aero model
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plot_section_polars draws cl, cd and cm against alpha per panel, for every aero model
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linearize and make_dual_shadow take a BodyAerodynamics with several wings
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stability_derivatives gives roll, pitch and yaw rate derivatives about solver.reference_point
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