二维非常规压缩型面超/高超声速进气道的设计概念

为了提高满足一定尺寸要求的进气道的性能,提出了一种非常规压缩型面进气道,并用数值模拟手段对该进气道和常规的二维斜楔式进气道的性能进行了比较。数值模拟结果表明,设计工况下该进气道能够获得跟常规二维斜楔式进气道大致相当的气动性能。非设计工况下,该进气道性能优于常规进气道。一体化设计时,该进气道对保持前机体来流附面层的稳定性十分有利。

Concept of a two-dimensional supersonic/hypersonic inlet with a non-conventional compression wall

An inlet with non-conventional compression wall is designed in order to improve the performance of inlets constrained by its size. Comparisons by means of numerical simulation are made between this inlet and the normal two-dimensional ramp inlet. It is shown that at the design point the inlet with the non-conventional compression wall has the similar performance as the normal one, but has a better performance at off-design point. This demonstrates that for propulsion-airframe integration, this genus of inlet would be advantageous in keeping the stability of boundary layer coming from the forebody.