关键词: 冲压式喷气发动机;超音速进气道;实验;研究

Abstract: The experimental results of two-dimensional inlet with boundary layer bleed slot installed at the upstream of the geometry throat are presented in this paper.The slot has different type of swept endwall, different slot width and slot exit area.The experiment was performed at free stream Mach numbers from 1.793 through 2.557 and at angle of attack from -6° through 10°.At the zero angle of attack, the flow pattern and the performance of inlets with and without bleed are compared.The effects of the boundary layer bleed flow and endwall on the performance of the inlet are discussed.The characteristic at different angle of attack is analysed.The terminate shock patterns in the inlet varied with the increase of downstream pressure are discribed.Video record shows that within the range of the bleed flow experimental model inlet demonstrates continuity in aerodynamic characteristic. Mamely,the terminate shock system pas-ses gradually through the bleed slot zone and results in a change from supercritical condition to subcritical condition, just like what happens in a supersonic external compressible inlet.

Key words: Ramjet engine;Supersonic inlet;Test;Research