Numerical investigation on properties of attack angle for opposing jet thermal protection system

doi:10.1088/1674-1056/21/8/084401

Abstract The three-dimensional Navier-Stokes equation and the k-ε viscous model are used to simulate the attack angle characteristics of a hemisphere nose-tip with an opposing jet thermal protection system in supersonic flow condition. The numerical method is validated by the relevant experiment. The flow field parameters, aerodynamic forces, and surface heat flux distributions for attack angles of 0°, 2°, 5°, 7°, and 10° are obtained. The detailed numerical results show that the cruise attack angle has a great influence on the flow field parameters, aerodynamic force, and surface heat flux distribution of the supersonic vehicle nose-tip with opposing jet thermal protection system. When the attack angle reaches 10°, the heat flux on the windward generatrix is close to the maximal heat flux on the wall surface of the nose-tip without thermal protection system, thus the thermal protection is failure.

Keywords: properties of attack angle opposing jet thermal protection system supersonic vehicle computer simulation

Received: 08 January 2012
Revised: 14 February 2012
Accepted manuscript online:

PACS:	44.05.+e	(Analytical and numerical techniques)
	47.40.Ki	(Supersonic and hypersonic flows)

Fund: Project supported by the National Natural Science Foundation of China (Grant No. 90916018), the Research Fund for the Doctoral Program of Higher Education of China (Grant No. 200899980006), and the Natural Science Foundation of Hunan Province, China (Grant No. 09JJ3109).

Corresponding Authors: Lu Hai-Bo
E-mail: lhbboo@sohu.com

Cite this article:

Lu Hai-Bo (陆海波), Liu Wei-Qiang (刘伟强 ) Numerical investigation on properties of attack angle for opposing jet thermal protection system 2012 Chin. Phys. B 21 084401

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