Numerical Simulation of the Second Mode Instability with the Local Wall Cooling/Heating
1 Introductions The development of secure and re-usable re-entry vehicle requires the complete control of the heat distribution on its Thermal Protection System (TPS). During the most critical re-entry phase, the hypersonic flow along the vehicle initiates a laminar boundary layer inside of which most of the transfer phenomena take place (heat, momentum and mass transfer). If at one position of the vehicle, this boundary layer experiences a transition from the laminar to the turbulent regime then at the corresponding position the TPS will receive a sharp increase of the incoming heat flux (minimum 3 times higher). If the vehicle aims to be re-usable, it is mandatory to protect it adequately against this overheat. Therefore aerospace designer needs to receive the proper information and tools allowing a better prediction and ultimately a better control of the transition in hypersonic regime.
P.A. Polivanov A.A. Sidorenko A.A. Maslov
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS 630090, Institutskaya, 4/1, Novosibirsk, Russia
国际会议
The 8th Sino-Russia High-speed Flow Conference(第八届中俄高超声速流体力学研讨会)
上海
英文
57-61
2011-11-21（万方平台首次上网日期，不代表论文的发表时间）