Numerical Investigation on Aero-Thermodynamic Characteristics of Wedge Shaped Nose Cone of Near Space Supersonic Flight

Abstract:

A numerical investigation on the space (0-46km) aero-thermodynamic characteristics of a nose cone model was performed using commercial software STAR-CCM++. Turbulence model and numerical calculation strategy was validated by the experimental phenomenon captured in a ground high-enthalpy wind tunnel and empirical formula calculation. The purpose of this paper is to discuss the distinctions between the experiment performed in ground high-enthalpy wind tunnel environment and real space flight using the validated numerical strategy, as well as the aero-thermodynamic characteristics of the nose cone model in different flight altitudes and Mach numbers, which will give a guidance to active cooling of spacecraft in real supersonic flight.

• Periodical: Applied Mechanics and Materials (Volumes 541-542)
• Pages: 608-612
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.541-542.608
• Online since: March 2014
• Authors: Jia Lin, Lian Jin Zhao, Jian Hua Wang
• Keywords: Leading Edge Nose Cone, Stagnation Point, Supersonic, Thermodynamic Characteristics

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