High subsonic and transonic effects on pressure distributions measured for a swept wing with oscillating control surface

Report (1970)
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Published Date

15-05-1970

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NLR MP 70011 U

Abstract

An analysis is given of pressure distributions measured on a swept wing model with harmonically oscillating control surface at subsonic to supersonic Mach numbers and at various frequencies. The influence of Mach number and finite span effects is discussed. Some comparisons are made with pressure distributions on a two-dimensional wing and with calculated results.

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