Research progress on high-enthalpy and hypersonic flows
The research progress on high-enthalpy and hypersonic flows having been achieved in theInstitute of Mechanics, Chinese Academy of Sciences, is reported in this paper. The paper consists ofthree main parts: The first part is on the techniques to develop advanced hypersonic test facilities, in which the detonation-driven shock-re ected tunnel and the detonation-driven shock-expanded tube areintroduced. The shock tunnel can be used for generating hypersonic flows of a Mach number rangingfrom 10 to 20, and the expansion tube is applicable to simulate the flows with a speed of 7～10 km/s.The second part is dedicated to the shock tunnel nozzle flow diagnosis to examine properties of thehypersonic flows thus created. The third part is on experiments and numerical simulations. Theexperiments include measuring the aerodynamic pitching moment and heat transfer in hypersonicflows, and the numerical work reports nozzle flow simulations and flow non-equilibrium effects on thepossible experiments that may be carried out on the above-mentioned hypersonic test facilities.
hypersonic flows detonation driver shock-re ected tunnels shock-expanded tube heat transfer
Z.Jiang H.R.Yu Z.B.Lin
LHD of Chinese Academy of Sciences, Institute of Mechanics, Beijing 100080, China
国际会议
The Fifth International Conference on Fluid Mechanics(第五届国际流体力学会议)
上海
英文
2007-08-15（万方平台首次上网日期，不代表论文的发表时间）