ESDU 82005
Linearised two-dimensional oscillatory airforce coefficients and load distributions on thin aerofoils in supersonic flow.
Abstract:
ESDU 82005 presents results, for use in flutter calculations, obtained from a computer program. The program embodies a method for evaluating the forces, moments and pressure distributions on a thin aerofoil oscillating harmonically with small amplitude in supersonic flow. The calculations were made for three modes of oscillation: aerofoil heave and pitch, and motion of a trailing-edge control surface with its hinge-line at 0.8 of the aerofoil chord. The results are presented in the form of tabulated airforce coefficients over a frequency parameter range from 0 to 2.0 and a Mach number range from 1.02 to 5.0. In addition, illustrative graphs are presented to show the effect of frequency and Mach number on oscillatory load distribution in heave and pitch.Indexed under:
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