弹用二元超声速进气道侧滑敏感性数值分析

Numerical analysis on sensitivity of supersonic 2-D inlet to sideslip

为评价二元超声速进气道在侧滑飞行条件下的适用性,基于Fluent软件,运用CFD数值模拟技术,开展了某实例二元超声速进气道内外流三维流场数值仿真计算,分析了有侧滑时进气道内部的流动性态,揭示出侧滑导致进气道迎风内侧壁附面层增厚,从而强化附面层对超声速扩压段斜激波和喉道段流动的干扰作用,使进气道捕获流量特性和总压恢复性能同步下降,侧滑角越大,进气道总体性能损失幅度越大。总体上,在0°~6°的小侧滑角范围内,因侧滑导致溢流造成进气道捕获流量的相对损失幅度低于3%,总压损失幅度不超过1.29%,表明在此条件下进气道总体性能对侧滑敏感性弱,仍可恰当适用。

To evaluate applicability of supersonic 2-D inlet under sideslip condition,CFD software,FLUENT,is used to carry out numerical simulation of internal and external 3-D flow fields for a supersonic 2-D inlet.The effect of sideslip on inlet internal flow characteristics is also analyzed.Results show that inlet inner wall boundary layer thickening due to sideslip will strengthen the affect of boundary layer on oblique shock system at supersonic diffuser and flow at throat,resulting in deterioration of both captured flow and total pressure recovery performances.And inlet overall performance loss increases with sideslip angle.Within 0° to 6° sideslip range,sideslip-caused captured flow loss and total pressure loss are less than 3% and 1.29%,respectively.Therefore,inlet overall performance is insensitive to sideslip and suitable for application under such situation.