Optimization and Experimental Investigation of 2-D Hypersonic Curved Shock Compression Inlet

摘要

For the two-dimensional hypersonic curved shock compression inlet, the reverse designing method according to the given law of wall pressure distribution combining with the multi-objectives optimization technique is investigated, and wind tunnel test is carried out to verify this method. The results show that high performance inlet could be obtained in this way. Under Mach 6 wind tunnel test, the optimized inlet system has a pressure ratio of 39.6, a total pressure recovery of 0.442, and the critical back pressure ratio would be higher than 195.