Investigation of Dynamic Characteristics for a Hypersonic Forebody/Inlet at Mach 6
Numerical and experimental researches on dynamic characteristics of a hypersonic mixed-compression, fixed-geometry forebody/inlet with throttling are conducted in this paper. The numerical research is that two dimensional, quasi-steady computational simulation at the symmetric plane of the three dimensional inlet is performed, which gives a preliminary result of dynamic characteristics in the inlet. The numerical research shows that the shock oscillations, as a character of inlet dynamic characteristics, behave certain periodicity. The numerical research also shows that a typical shock propagation process in every period of the shock oscillation demonstrates as follows, the shock generated by back pressure, transmits forward and disgorged by the internal tube at first, then destroys the shock system of the external compression, and again swallowed by the internal tube till the shock system of the inlet is rebuilt. Based on the CFD work, a dynamic experimental research of the inlet is then carried out in CARDC ∮0.5m blowdown cold-flow wind tunnel at Mach number 6 to get the shock oscillation characteristics of the inlet under different throttled conditions. A dynamic pressure data acquisition system is used to sample and record the dynamic pressure signal data. At the same time, a high frequency CCD video is used to record the schlieren pictures of the internal flow synchronously. The results of the dynamic characteristics of the inlet at Ma6 are obtained from comparison between the previous computational research and the current experimental research. These results can provide an important support for the further validation of the CFD, the internal flow design of self-start inlets, the process analysis of the internal dynamic oscillation, and the mechanics research of the shock oscillation.
dynamic characteristics hypersonic forebody/inlet shock oscillation
Yu Anyuan Le Jialing Ni HongLi Yang DaWei Liu WeiXiong
Air-breathing Hypersonic Technology Research Center, CARDC Science and Technology on Scramjet Laboratory, Mianyang, P.R.China, 621000
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
88-95
2011-11-21（万方平台首次上网日期，不代表论文的发表时间）