Abstract
The problem of flow around a V-shaped wing with supersonic leading edges is solved. The method employed is that of fitting with respect to a space variable in which the system of equations of motion is hyperbolic, using the computing scheme of V. V. Rusanov, A comparison between the results of these calculations and experimental data in relation to the pressure distribution along the wing span reveals excellent agreement, except for a limited region, in which the compression jump incident on the plane of the wing interacts with the boundary layer. A comparison between the results obtained by means of the oblique-jump equations and by numerical calculations indicates that the method in question is reasonably accurate.
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Translated from Izvestiya Akademu Nauk SSSE, Mekhanika Zhidkosti i Gaza, No. 3, pp. 180–185, May–June, 1971.
The author is grateful to A. L. Gonor and V. V. Rusanov for interest in this work.
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Lapygin, V.I. Calculation of supersonic flow around v-shaped wings by the fitting method. Fluid Dyn 6, 529–534 (1971). https://doi.org/10.1007/BF01014010
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DOI: https://doi.org/10.1007/BF01014010