摘要
无隔板进气道(DSI)具有宽马赫数性能好与结构简单等优点,已成功应用于美国F35飞机和中巴合作枭龙飞机的进气道设计。超声速飞行条件下进气道入口处鼓包(Bump)外形对进气道流动特性影响很大,直接影响着进气道性能。基于离散伴随方法求取梯度,采用序列二次规划(SQP)优化方法对鼓包外形进行优化。鼓包的外形参数化采用自由型面变形技术(NFFD),在外形改变后采用改进型距离函数法(IDWF)变形计算网格。结果表明,在畸变指数不增的约束条件下,优化后的进气道性能明显提高,总压恢复系数提高约5%,同时畸变指数下降约0.03。
The diverterless supersonic inlet( DSI) has been successfully applied for inlet design of USA fighter F35 and China-Pakistan cooperation aircraft JF-17,which is suitable for wide range of Mach number and easy to design of structure. The shape of bump before the air intake of inlet has a great influence on the flow character with a supersonic flight speed,which directly affects the performance of DSI inlet. With gradient calculated by discrete adjoint method,the sequential quadratic programming( SQP) optimization technique is applied for bump shape optimization. The NURBS based free-form deformation( NFFD) is adopted for shape parameterization and the improved distance weight function technique( IDWF) is used for computing grid deformation after bump shape is changed. The optimization results indicate that,with the constraint that the distortion index of the inlet is not allowed increase,the performance of inlet has been obviously improved,of which total pressure recovery coefficient increases about 5% and distortion index decreases 0. 03.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2017年第S1期77-81,共5页
Journal of Northwestern Polytechnical University
关键词
外形优化
DSI进气道
离散伴随
自由型面变形
网格变形
shape optimization
DSI inlet
discrete adjoint method
free-form deformation
grid deformation
