新型曲面压缩的高超侧压式进气道数值仿真

为进一步提高侧压式进气道性能，提出了变侧压角与变后掠角+变侧压角两种新型曲面压缩的侧压式进气道设计方案，利用数值仿真手段对其M6、M4下的流场结构及总体性能开展了研究，并与常规平面压缩的侧压式进气道进行了比较。结果表明，曲面压缩的侧压式进气道性能要明显优于常规平面压缩的进气道；采用变后掠角+变侧压角设计的曲面侧压式进气道具有前掠与后掠两种进气道的优点，能显著提高进气道高低马赫数下的性能。计算发现，马赫6设计点下，变后掠角+变侧压角的曲面侧压式进气道流量系数较常规进气道提高4.1%，总压恢复提高5.3%，二者之和为9.4%；马赫4来流条件下，流量系数提高6.3%，总压恢复提高5.4%，二者之和为11.7%。

Numerical Simulations of new generic curved surface sidewall compression scramjet inlets

Two generic curved surface sidewall compression scramjet inlets with varied compression angle or sweep angle were studied to improve the performance of the conventional plane compression sidewall compression inlet. The flow field structures and overall performance were invested comparatively at Ma=4 and 6 by means of numerical simulations, and comparisons were made between the new concept inlets and the conventional inlet. Results indicate the performance of the curved surface inlets was obviously superior to the conventional inlet. The new sidewall compression scramjet inlet with varied sweep angle and compression angle has the advantages of both backward and forward sweep sidewall compression inlet, which has smaller spillage angle at cowl place, weaker cowl shock waves and more stable boundary layer on the top wall. Numerical simulations also show that, at Ma=6 design point, the mass capture ratio of the new curved surface inlet with varied sweep angle was increased by 4.1% than that of the conventional inlet, and the total pressure recovery was increased by 5.3%; at Ma=4 starting point, the mass capture ratio was increased by 6.3%, the total pressure recovery was increased by 5.4%.