Laminar Boundary Layer with Foreign Gas Injection on a Conical Body
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概要
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The present paper deals with the theory of laminar boundary layer on a nonaxisymmetric conical body at supersonic flight with special reference to the effect of foreign gas injection (or "mas injection") on the body surface. The over-all flowfield over the conical body with nearly circular but otherwise arbitrary cross-section at small angles of attack is analytically solved using small perturbation method. The inviscid flow solution served as boundary layer edge conditions is obtained by an extension of the Stone's solution for a circular cone to the cases of nonaxisymmetric conical bodies. The similar boundary layer equations with a specific distribution of the mass injection rate inversely proportional to the square root of the meridional distance from the body apex are derived for the case of a binary mixture of nonreacting gases. An exact, first order perturbation solution not depending on flew parameters is presented, corresponding to the inviscid conical flow solution. The effects of mass injection on three-dimensional boundary layer characteristics are discussed for the cases of several shapes of conical bodies. The analytical results demonstrate a significant effect of mass injection on the boundary layer flow, especially on the local heat transfer and skin friction.
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