马赫数4~7的高超侧压式进气道气动设计与性能

金志光; 张堃元; 刘媛

马赫数4~7的高超侧压式进气道气动设计与性能

南京航空航天大学能源与动力学院,南京 210016

基金项目: 南京航空航天大学青年科技创新基金(NS2010039)

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出版历程
- 收稿日期: 2010-05-13
- 修回日期: 2010-12-14
- 刊出日期: 2011-06-28

Design and performance investigation of sidewall compression scramjet inlets operating from Mach 4 to Mach 7

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

摘要

摘要: 对巡航马赫数为7、转级马赫数为4的宽范围侧压式进气道进行了设计,讨论了主要设计参数的选取原则,给出了一种曲面压缩的高性能侧压式进气道设计方案,并利用数值仿真手段对其流场结构及性能进行了研究.结果表明,所设计的侧压式进气道在马赫数Ma=4时的流量系数达到0.753,最大正攻角可达6°以上.Ma=6时,流量系数达到0.945,隔离段出口总压恢复系数为0.504.Ma=7时,总压恢复系数为0.388;随攻角增加,进气道捕获流量几乎线性增加,流场畸变有所减小,但总压恢复系数加速下降;随侧滑角增加,总压恢复系数下降剧烈,流量系数变化不大.研究还发现,进气道下游的三维隔离段其上下壁面压差导致隔离段底部形成“对涡”流动,显著加大了流场畸变,这是各类三维隔离段的典型流动特征.
- 超燃冲压发动机进气道 /
- 侧压式进气道 /
- 曲面压缩 /
- 攻角特性 /
- 侧滑角特性 /
- 数值仿真
Abstract: Three-dimensional sidewall compression scramjet inlets with fore body compression operating in a large Mach number range from 4 to 7 were designed.The selection principles of the inlet primary design parameters were discussed and a high performance inlet scheme with curved surface compression was given.The complex flow field structure and the global performance of the scramjet inlet were investigated by means of numerical simulations.Results indicate at Mach 4 starting point,the sidewall compression scramjet inlet has a mass capture ratio of 0.753 ,and can work at above 6 degrees attack angle.At Mach 6,the inlet has a mass capture ratio of 0.945 and a total pressure recovery coefficient of 0.504 at the isolator exit,and 0.388 at Mach 7 cruising point.Numerical simulations also show that with the increasing attack angle,the captured mass flow increases nearly linearly,but the total pressure recovery coefficient decreases dramatically.As the yaw angle increased,the inlet total pressure recovery coefficient also decreases dramatically,but the mass capture ratio only drops slightly.It is also found that a pair of vortex occurre at the bottom of the isolator because of the pressure difference between the upper and lower walls of the isolator entrance,which increase the flow field distortion,and decrease the total pressure along the isolator.
- scramjet inlet /
- sidewall compression scramjet inlet /

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参考文献(12)

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