Abstract
This paper presents an analysis of the combinations of wings and conical bodies of arbitrary cross section in supersonic flow. Particular emphasis is given to the delta wing and elliptic cone combinations, for which analytical solutions are obtained for the spanwise variation of the lifting load coefficient. Cases of subsonic and supersonic leading edges are both equally treated. In this formulation, the wing incidence is allowed to change along the span, as in the case of wing/body systems with leading-edge flaps, or with a continuously variable wing incidence. The effect of the wing thickness is also discussed. The theoretical solutions obtained for the delta wing and elliptic cone systems are in good agreement with Jorgensen's experimental results for various Mach numbers, wing spans, and cross-sectional semiaxis ratios. Good agreement with the experimental results is also obtained in the limit case of isolated elliptic cones.
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