Conditions for excitation of vibrations of aerodynamic control surfaces in an attached transonic gas flow
This article examines the conditions for excitation of vibrations of aerodynamic control surfaces in a transonic gas flow with shock waves. It is shown that the hinge moments with the largest exciting effect, due to features of the interaction of the vibrating control surfaces with the shock waves, are seen when the Mach numbers M of the undisturbed flow are such that the shocks are located near the trailing edge of the airfoil. Approximate analytic expressions are obtained which make it possible to evaluate the maximum exciting hinge moments for control surfaces. A graphical interpretation of these expressions is also presented.
KeywordsShock Wave Mach Number Control Surface Exciting Effect Graphical Interpretation
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