Experimental Analyses of Inlet Characteristics of an Airbreathing Missile with Boundary-Layer Bleed

Abstract

The performance of different boundary-layer bleed systems of a two-dimensional ramjet inlet has been investigated experimentally. The main objective of the study has been to identify the correlation between the inlet’s performance with different boundary-layer bleed geometries and the inlet’s internal flow. Experiments have therefore been carried out with varied boundary-layer bleed geometries at an angle of attack of 0 deg and at Mach numbers ranging from 2.5 to 3.5 in the Trisonic Wind Tunnel Cologne. The results are a continuation of an earlier study and show that the inlet’s performance and the effectiveness of boundary-layer bleed system depend on shock/boundary-layer interaction, unsteadiness of the flow, and flow separation.