Journal of Applied Science and Engineering

Published by Tamkang University Press


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Qin Luo1, Yu-Hua Chen1, Feng-Juan Ju1 and Guang-Ming Guo This email address is being protected from spambots. You need JavaScript enabled to view it.2

1College of Information Engineering, Jiangxi University of Technology, Nanchang 330098, P.R. China
2School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, P.R. China


Received: August 2, 2016
Accepted: January 7, 2017
Publication Date: June 1, 2017

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Near space has been paid more and more attentions in recent years due to its military application value and flying vehicles in near space usually have hypersonic speeds. The temperature distribution of aerodynamic flow field over optic window of optical seeker of a flying vehicle is quite non-uniform and has a great temperature gradient due to the strong shock wave and aerodynamic heating. The direct simulation Monte Carlo based on Boltzmann equation was used for computations of aerodynamic flow surrounding optical seeker. Both mean temperature contour over optical window and temperature profiles along the vertical and horizontal lines at some specific locations nearby optical window were provided to quantitatively investigate temperature distribution characteristics over optical window in near space. Several cases, in which the altitude, without/with cooling jet, and flight Mach number were taken into account, were performed to research temperature distribution characteristics in detail. The results indicated that temperature distribution was affected observably by altitude and Mach number, and the cooling jet is able to drastically reduce the temperature gradient nearby the optic window.

Keywords: Temperature Distribution, Optical Window, DSMC, Near Space, Hypersonic


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