关键词: 风洞试验;外压式进气道;设计参数;进气道气流;实验空气动力学

Abstract: A 1/11-scale model of a two-dimensional external compression supersonic inlet with maximum Mach number 1. 8 was tested from Mach 0. 8 to 1. 8. Theramp of the inlet is side-mounted vertically, its duct is bifurcated. The effects oframp angles, internal lip angles and circle lip radius on internal performances of theinlet are presented. The experimental results show that a small change of ramp angle causes large changes of inlet pressure recovery, circumferential steady-pressuredistortion and buzz margin, and small changes of internal lip angle and lip radius effect the changes in performances of inlet unobviously at subsonic, but apparently atsupersonic.

Key words: Wind tunnel test;External compression inlet;Design parameter;Inlet flow;Experimental aerodynamics