The invention discloses a high-speed air inlet passage inlet precursor based on integral controllable ridge type pressure distribution, which is a three-dimensional ridge type pressure distribution Bump profile. The high-speed air inlet passage inlet precursor is generated by the following steps of (1) determining a parabolic precursor contour line according to an intersection line between a selected basic flow field and an interception plane, (2) with the midpoint of the opening position of the precursor contour line as the center, sweeping along the circumferential direction of the precursorcontour line to obtain a plurality of discrete two-dimensional molded lines, (3) arranging a ridge type pressure distribution curve on each two-dimensional molded line, wherein a plurality of ridge type pressure distribution curves form a quasi-circumferential pressure distribution cluster, and (4) finally, obtaining a three-dimensional ridge-type pressure distribution Bump profile of the precursor based on the pressure distribution reverse profile. The hypersonic boundary layer is efficiently displaced, the external resistance of the front body and the flow field uniformity of the middle rear part of the Bump are reduced, and the arrangement of a hypersonic air inlet passage is facilitated.
本发明公开一种基于整体可控山脊式压力分布的高速进气道进口前体,该前体为三维的山脊式压力分布的Bump型面,其生成步骤为:(1)由选定的基本流场和截取平面之间的相交线确定一呈抛物线状的前体轮廓线;(2)以前体轮廓线的开口位置的中点为中心,沿前体轮廓线周向扫掠,得到若干离散的二维型线;(3)在每条二维型线上布置山脊式压力分布曲线,若干山脊式压力分布曲线组成准周向压力分布簇;(4)最后基于压力分布反求型面得到前体三维的山脊式压力分布的Bump型面。本发明兼顾高效排移高超声速附面层、减小前体外部阻力,以及Bump中后部的流场均匀性,有利于布置高超声速进气道。
High-speed air inlet passage inlet precursor based on integral controllable ridge type pressure distribution
基于整体可控山脊式压力分布的高速进气道进口前体
2020-10-27
Patent
Electronic Resource
Chinese