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YASim: Difference between revisions
→wing: new features flow and mcrit
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* '''effectiveness:''' Multiplier for the "normal" drag generated by the wing. Defaults to 1. Arbitrary, dimensionless factor. | * '''effectiveness:''' Multiplier for the "normal" drag generated by the wing. Defaults to 1. Arbitrary, dimensionless factor. | ||
* '''camber:''' The lift produced by the wing at zero angle of attack, expressed as a fraction of the maximum lift produced at the stall AoA. | * '''camber:''' The lift produced by the wing at zero angle of attack, expressed as a fraction of the maximum lift produced at the stall AoA. | ||
* '''flow:''' The flow regime for the wing. Valid values are "SUBSONIC" (default) and "TRANSONIC". Setting surface to transonic adds more lift above mach number 0.6 by applying a Prandl/Glauert correction term to each surface-element. The effect is a more balanced lift/drag distribution reported by the solver. Use for anything that flies faster than mach 0.6 or has supercritical airfoils. | |||
* '''mcrit:''' The critical mach number for the wing. This point defines the begin of exponential drag rise due to mach speed. Default "0.6", only available if flow="TRANSONIC". | |||
''' | '''Wing section support (since 2018.1):''' | ||
Wing section support to define variable geometry (geometry parameters per section) | Wing section support to define variable geometry (geometry parameters per section) | ||