Hypersonic large-deflection similitude for oscillating delta wings

Abstract

AbstractA similitude has been obtained for delta wings with attached leading edge shock at large incidence in hypersonic flow. A strip theory in which flow at a spanwise location is two-dimensional has been developed. This combines with the similitude to lead to a piston theory which gives closed form solutions for unsteady derivatives in pitch and roll. The derivatives in pitch are independent of and the roll damping derivative varies linearly with the aspect ratio. Substantially the same results as the theory of Liu and Hui are obtained with remarkable computational ease.