The modeling of high-speed flows stipulates also the compliance with other similarity criteria, which includes first of all the criteria of Mach numbers (M) and Reynolds numbers (Re), as well as ensuring the low level of turbulence and flow homogeneity in the facility working section. The method of model fixation also influences significantly the accuracy of the experiment. The simultaneous solution of these problems within one experimental facility seems to be impossible. In the extreme case of free-molecular flow, the integral of collisions in the Boltzmann equation becomes zero, and its general solution is a boundary function of distribution, which remains constant along the paths of particles [1]. In the transitional regime, the most suitable method to compute heat transfer coefficient of hypersonic vehicle relies on bridging formulae [2]. In order to determine the force action and heat action of the gas on the body, it is sufficient to know local exchange coefficients of impulse and energy.
Fig. 1. Heat transfer coefficients Ch (a) for “Clipper” (blue) and “Falcon HTV-2” (red) [2]
The reported study was partially supported by the Russian Foundation for Basic Research (Research project No. 14-07-00564-а).
The work is submitted to the International Scientific Conference "MODERN HIGH TECHNOLOGIES", Israel, April25 -2 May, 2014, came to the editorial office оn 02.04.2014
Библиографическая ссылка
Khlopkov Yu.I., Zharov V.A., Khlopkov A.Yu., Zay Yar Myo Myint Mathematical modeling of aerothermodynamic characteristics for hypersonic vehicles // Международный журнал экспериментального образования. – 2014. – № 6. – С. 29-30;URL: https://expeducation.ru/ru/article/view?id=5838 (дата обращения: 27.09.2024).