Investigation of a Fluidic Shock Control Method for Hypersonic Inlets
In order to provide a fixed-geometry shock control technique for hypersonic inlets, the current study involves a fluidic shock control method. An integrated analysis and design method is developed and verified by two-dimensional viscous simulations though the accuracy is not so satisfactory due to the neglect of the momentum loss caused by wall friction and the interactions between the secondary flow and the primary flow. A demonstration of the first ramp shock control by wind tunnel tests and three-dimensional viscous simulations shows that the fluidic shock control technique can meet the shock control requirement of hypersonic inlets operating from Mach 4 to Mach 6. The shock displacement at the duct entrance increases monotonously and smoothly with the increase of the secondary flow rate. At a secondary to primary mass flow ratio of 1％ or less the first ramp shock can be maintained on the cowl lip from Mach 5 to Mach 6. On average, no extra total pressure loss caused by the curved shock is observed. Also the mixed boundary layer is found fairly stable at the ramp corner.
shock control hypersonic inlet
Cheng-hong Li Hui-jun TAN Yue Zhang
College of Energy and Power Egineering Nanjing University of Aeronautics and Astronautics 210016 Nanjing, Peoples Republic of China
国际会议
The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)
南京
英文
127-139
2010-09-13（万方平台首次上网日期，不代表论文的发表时间）