Unsteady aerodynamics for wings with control surfaces

Report (1970)
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Published Date

31-12-1970

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NLR MP 71009 U

Abstract

A kernel function method for calculating pressure distributions over wings with harmonically oscillating control surfaces in subsonic flow is briefly discussed. Comparisons of calculated and measured pressure distributions are given for different planforns, Mach numbers and reduced frequencies. An analysis is presented of pressure distributions measured at high subsonic and transonic Mach numbers.

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