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Heat transfer to blunt-edged swept wings at angle of attack in hypersonic flow

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Abstract

An approximate analytic solution is obtained for the relative heat fluxes on the lateral surface of swept wings of infinite span in a hypersonic viscous gas flow at angles of attack and yaw. The accuracy of the relations obtained is estimated on the basis of a comparison with numerical solutions.

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Authors
  1. I. G. Brykina
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Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 4, pp. 170–179, July–August, 1994.

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Brykina, I.G. Heat transfer to blunt-edged swept wings at angle of attack in hypersonic flow. Fluid Dyn 29, 577–584 (1994). https://doi.org/10.1007/BF02319081

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  • DOI: https://doi.org/10.1007/BF02319081

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