Engineering Methods to Calculate Heat Transfer Coefficients on the Surface Body in High-Speed Flow
[1]
Zay Yar Myo Myint, Department of Aeromechanics and Flight Engineering, Moscow Institute of Physics and Technology, Zhukovsky, Russia.
[2]
Sergey Lvovich Gorelov, Department of Aeromechanics and Flight Engineering, Moscow Institute of Physics and Technology, Zhukovsky, Russia.
The development of rocket and space technology is very important for any countries for two categories: construction high-speed passenger plane and reusable aerospace vehicle. It’s required continuous improvement of the research of processes of heat and mass transfer, and heat transfer theory development. Modeling research allows to quickly analysis the aerodynamic and heat exchange processes of high-speed aircrafts by using theoretical and experimental research. Well known method - Direct simulation Monte Carlo method (DSMC) is the basic quantitative tool for study of high-speed rarefied gas flow. These methods remain the most reliable approach, together with the local engineering methods, that provides good results for the global aerothermodynamics coefficients. Engineering methods are required small amount of computer resources (i.e. memory) and expensive at the initial stage of aircraft design and trajectory analysis. There are many engineering methods to calculate aerothermodynamics in hypersonic flow. In this paper described the analysis of the engineering methods to predict heat transfer coefficient on the surface of high-speed aircraft at high-altitude.
High-Speed Aircraft, Bridging Methods, Transitional Flow Regime, Rarefied Gas Dynamics, Heat Transfer in Boundary Layer
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