二维超音速进气道性能实验研究

介绍几何喉道上游具有不同进口侧板、不同槽宽的附面层吸除槽和槽腔出口不同放气孔面积的二维超音速进气道,在自由流马赫数:Ma_∞=1.793,2.037,2.292,2.557;攻角:α=0°,3°,6°,10°,-6°条件下的实验研究结果。讨论了零攻角下,有无吸除时进气道的流型、性能和不同侧板、吸除槽宽、放气孔面积对进气道性能的影响。分析了二维超音速进气道的攻角特性;描述了进气道结尾波系随下游反压增高时的波系演变图案,录相显示了具有一定槽宽、一定吸除量的实验模型具有连续的气动特征,如同全外压式进气道那样,结尾波系从超临界连续地通过槽区到达亚临界。

EXPERIMENTAL INVESTIGATION ON PERFORMANCES OF TWO-DIMENSIONAL INLET AT SUPERSONIC SPEED

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.