摘要
对内收缩进气道的设计方法进行了改进,在原有方法中加入了形面渐变技术。内收缩进气道的基准流场采用变斜率母线内收缩锥形流场,相较于定斜率母线基准流场,能够在不降低增压比的条件下同时提高总压恢复和流动均匀性,有利于进气道性能提升。进气道唇口形状选用类椭圆形以提升进气道气动特性,应用形面渐变技术保证进气道与发动机入口的匹配。研究发现,平方融合函数P2能够较好的抑制形面渐变对进气道性能的不利影响。数值模拟结果表明,进气道在设计点工况下性能良好,出口流动均匀性较好。
An advanced design method of inward turning inlet was proposed, which included a shape morphing technology. The basic flow used in the design process was a flow inside a cone with varied slope generatrix. Compared with the conventional basic flow, this type of basic flow was able to improve the performance of total pressure recovery and flow uniformity without the compression loss, which was beneficial to enhance the inlet working efficiency. A quasi-oval lip was employed to promote the inlet aerodynamic characteristic, while the shape morphing technology was used to make sure that the inlet and engine can be integrated well. Related research indicates that the p2 blending function is helpful to alleviate the negative influence of shape morphing on the overall performance. Numerical simulation results show that the inlet works well with high level flow uniformity on the design point.
作者
王骥飞
蔡晋生
WANG Jifei CAI Jinsheng(School of Aeronautics, Northwestern Polytechnical University, Xi＇an 710072, China)
出处
《航空科学技术》
2017年第1期30-35,共6页
Aeronautical Science & Technology
关键词
高超声速飞行器
进气道
优化设计
流线追踪
数值模拟
hypersonic aircraft
inlets
design optimization
streamline trace
numerical simulation
