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FLOW OF THIN WINGS BY HYPERSONIC FLOW OF RELAXING GAS

By Georgy Nikolaevich Dudin

Abstract

The law of plane cross sections for the three-dimensional boundary layer on the thin wings of small elongation in hypersonic flow has been determined. The boundary problems have been formulated, the solutions of flowing half-infinite wings and finite length wings in the different conditions of viscous-non-viscous interaction have been obtained. The concrete numerical results and similarity parameters have been obtained, the numerical methods which can be used in the experimental and computing aerodynamics and also at designing of the hypersonic aircrafts (HA) with high quality coefficient have been developed. The mathematical models of flows with return cross flows have been obtained, the finite value disturbance transmission fields which denermined the surface heat transfer and efficiency of the aerodynamic control elements have been determined. The obtained results can be used in the organizations possessing the investigation and designing of HAAvailable from VNTIC / VNTIC - Scientific & Technical Information Centre of RussiaSIGLERURussian Federatio

Topics: 20I - Fluid mechanics, MATHEMATICS, MECHANICS, MECHANICAL ENGINEERING
Year: 1992
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Provided by: OpenGrey Repository
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