Wave Interactions in Transonic and Hypersonic Flow.
Final scientific rept. 1 Dec 70-30 Nov 75,
ROCKWELL INTERNATIONAL THOUSAND OAKS CALIF SCIENCE CENTER
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Studies in the transonic and hypersonic regime of nonlinear flows are summarized. In the approximation of weak three-dimensionality, area rules have been developed which predict aerodynamic efficiencies of flat top conical wingbody combinations consisting of conically subsonic conical bodies mounted on the windward side of hypersonic delta wings. Investigations of the pressure fields and shock waves over these combinations are discussed from the stand-point of cross-flow stagnation singularities. The generalization of these results to non-conical supersonic conical bodies are also indicated. For the former, an extended area rule has been derived indicating that the increment in lift due to body addition depends on an area progressing at successive reflection of a two-dimensional disturbance emanating from the body with the shock. Upper bounds for LD benefits and optimum fuselage shaping are indicated. In the case of conically supersonic conical bodies, the subcritical area rule is demonstrated to remain valid. Pressure fields for this class of configurations reveal a wave train structure. The reflection coefficients, intensity, and number of reflections are quantified in terms of the supercriticality of the secondary leading edge. For the aspect of the research dealing with transonic flow, asymptotic results for the far field derived for supercritical jet flaps subject to solid tunnel wall interference are also discussed. Author
- Fluid Mechanics