Abstract
A method based on the use of the two-approximation theory developed in [1, 2] is proposed for the computation of hypersonic flow past a conical wing with a Mach-type shock configuration.
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Literature Cited
A. L. Gonor, “Hypersonic flow past a delta wing,” Prikl. Matem. Mekhan.,34, No. 3, 481 (1970).
A. L. Gonor and N. A. Ostapenko, “Hypersonic flow past a delta wing of finite thickness,” Izv. Akad. Nauk SSSR, Mekhan. Zhidk. i Gaza, No. 3 (1970).
A. L. Gonor and A. I. Shvets, “Investigation of the system of compression shocks arising in a flow past a star-shaped body,” Izv. Akad. Nauk SSSR, Mekhan. Zhidk. i Gaza, No. 3 (1966).
A. L. Gonor, V. I. Lapygin, and N. A. Ostapenko, “The conical wing in hypersonic flow,” paper presented at the Second Conference on Numerical Methods in Fluid Dynamics, University of California, Berkeley, USA (1970).
G. I. Maikapar, “The wave drag of nonaxisymmetric bodies at supersonic velocities,” Prik. Matem. Mekhan.,23, No. 2 (1959).
Additional information
Moscow. Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 104–116, May–June, 1972.
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Gonor, A.L., Ostapenko, N.A. Hypersonic flow past an airfoil with a mach system of shock waves. Fluid Dyn 7, 455–465 (1972). https://doi.org/10.1007/BF01209051
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DOI: https://doi.org/10.1007/BF01209051