乘波构型前体/进气道一体化设计仿真研究

Integrated Design and Performance Contrast Research of Waverider Configration Forebody/Inlet

研究了源于锥形流场乘波构型、源于相交锥流场乘波构型和密切分析法乘波构型三种比较有应用潜力的高超声速乘波构型前体。开展了对三种乘波构型前体气动性能的仿真计算和评估,为高超声速飞行器乘波前体/进气道一体化设计提供了参考。分析结果表明:具有单道前缘封闭激波的源于锥形流场的乘波构型应用价值有限,而具有三道封闭压缩激波的相交锥乘波构型和密切分析法乘波构型在完成相同压缩任务的条件下表现出了较大优势。在进气道进口截面处边界层厚度近似相等的情况下,后两种构型进气道总压恢复系数相比第一种构型分别提高了21.2%/和17.6%,流量系数分别提高了3.6%和1%,进气道出口截面流场不均匀度分别降低了8.9%和5.1%。

Three kinds of hypersonic waverider configuration forebodys based on cone flow field,intersected cones flow field and osculation analysis method were investigated contrastively.The numerical simulation and performance evaluation were carried out for these three configuration forebodys in this paper.The work provides reference for integrated design of hypersonic waverider configuration forebody/inlet.The analysis results show that the application of waverider configuration based on cone flow field which has one leading edge attached shock was limited.Under the circumstance of finishing the same compression task,the advantage is very obvious for waverider configurations based on intersected cones flow field and osculation analysis method with three attached shocks.Compared with the waverider configuration forebody based on cone flow field,the total pressure recovery coefficients of inlet for another two configurations were increased by 21.2% and 17.6%,respectively.The flow coefficients of inlet were increased by 3.6% and 1% respectively.The distortion coefficients of inlet were decreased by 8.9% and 5.1% respectively.