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

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.