Abstract
Improved methods for predicting aerodynamics of lifting surfaces are needed at the very low aspect ratios found in wing (housing) designs of span limited missiles and at moderate supersonic to hypersonic Mach numbers. A successful empirical method for estimating the normal force coefficient, CN, and center of pressure location, Xcp, for this class of surfaces has been developed for unbanked ( = 0 deg) cruciform wing configurations and for wing configurations banked at = 45 deg. The values of CN and X^ obtained using these empirical curves provide good estimates at Mach numbers above 2.5, and for angles-of-attack to 20 deg for thick and thin surfaces mounted in cruciform on cylindrical bodies.
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