The mode of attached compression shock at edges of a V-shaped wing: PMM, vol. 43, no. 1, 1979, pp. 38–44

• Published in: Journal of applied mathematics and mechanics Vol. 43; no. 1; pp. 39 - 45
• Main Authors: Grishin, A.V., Shifrin, E.G.
• Format: Journal Article
• Language: English
• Published: Elsevier Ltd 1979
• ISSN: 0021-8928; 0021-8928
• DOI: 10.1016/0021-8928(79)90120-5

The problem of supersonic flow past a V-shaped wing is considered in transonic approximation. The behavior of solution for modes close to the flow with a plane compression shock stretched over the [wing] edges is investigated in linear formulation. The mathematical problem reduces to the Riemann boundary value problem for analytic functions. The flow properties are investgated at small perturbations of the oncoming stream velocity. It is shown that when a plane compression shock at the wing edges in a plane normal to the edge is weak, the character of the flow is unaffected by variation of the Mach number. If, however, the shock in the main flow is strong, a rearrangement of the stream pattern is induced by a change of flow parameters. The considered problem is related to that of flow around star -shaped bodies investigated in [1−5]; the processs of rearrangement of the mode of flow past a V-shaped wing was analyzed by numerical methods in [6] and investigated experimentally in [7].