流线追踪Busemann进气道马赫数3.85实验研究

基金项目: 国家“八六三”基金项目(2003AA723020)

Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要: 为了研究流线追踪Busemann进气道在低马赫数来流条件下的起动性能、总体性能以及抗反压能力, 对设计马赫数5.3、收缩比CR=5的6°截短后的流线追踪进气道进行了马赫数3.85风洞实验.结果表明:该进气道在马赫数3.85来流条件下能够自起动;进气道流量系数为0.83, 出口总压恢复0.78, 马赫数2.01, 增压比11.92;进气道能够承受的最大反压为34倍的来流静压.
- 航空、航天推进系统 /
- 超燃冲压发动机 /
- Busemann进气道 /
- 流线追踪 /
- 风洞实验
Abstract: A wind-tunnel testing of a streamline traced hypersonic Busemann inlet,with a designed Mach 5.3 and shrinkage ratio CR=5,was conducted at Mach 3.85 to study its starting and overall performance as well as back-pressure capability below Mach 5.3 conditions.The results show that,the inlet can be started automatically at Mach 3.85;the flow coefficient of inlet is 0.83,the overall pressure recovery coefficient is 0.78,with a Mach number 2.01 and a compression ratio of 11.92;the inlet can withstand a maximum back-pressure of 34 times static pressure.
- aerospace propulsion system /
- scramjet /
- Busemann inlet /
- streamline traced /
- wind-tunnel testing

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