Abstract
The assumption of flow symmetry is made to investigate a supersonic flow (M∞ = 5) past a thin circular cone with a half-angle θ c = 4° and an isothermal surface (T w0 = 0.5) by way of numerical integration of unsteady-state three-dimensional Navier-Stokes and Reynolds equations. The calculations are performed in a discrete range of variation of the Reynolds number (104 ≤ Re ≤ 108) and angle of attack (0° ≤ α ≤ 15°). The effect of the determining parameters of the problem on the structure of flow field and on aerodynamic heating of the body surface subjected to flow is demonstrated.
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Translated from Teplofizika Vysokikh Temperatur, Vol. 43, No. 5, 2005, pp. 732–744.
Original Russian Text Copyright © 2005 by V. A. Bashkin, I. V. Egorov, and V. V. Pafnut'ev.
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Bashkin, V.A., Egorov, I.V. & Pafnut'ev, V.V. Aerodynamic Heating of a Thin Sharp-Nose Circular Cone in Supersonic Flow. High Temp 43, 733–745 (2005). https://doi.org/10.1007/s10740-005-0118-0
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DOI: https://doi.org/10.1007/s10740-005-0118-0