摘要
利用NURBS(non-uniform rational B-spline)曲线成功实现了涡控蛇形进气道参数化描述,并运用数值仿真方法对其中两个关键设计参数进行参数化研究.仿真结果表明:①第二S弯上壁面两侧后掠状凸起型面诱导的受控旋涡能够将低能流牵引至出口两侧,从而抑制大范围的气流分离,但凸起角取值需权衡选取,否则将不利于涡控蛇形进气道综合性能的改善.②通过抬高第二S弯下壁面能够减缓上壁面沿程逆压力梯度,进而影响第二S弯上壁面的流态,恰当的取值能够以微小的总压损失换取大幅度的畸变改善.③当设计参数选取恰当时,涡控蛇形进气道在设计状态下总压恢复系数为0.966 7,畸变指数为0.245 1.进气道性能较传统方案有显著改善,使得蛇形进气道迈向工程实用成为可能.
A parametric description method was established using NURBS （nonuniform rational Bspline） curve, and effects of two key parameters on the inlet performance were studied by numerical simulation. Results show.（1） Controlled vortex induced by backswept convex pon the second Sduct can lead low momentum flow to side regions of AIP （aerody namic interface plane）, and the separation region can be reduced. The value of convex angle need to be selected appropriately, otherwise the convex angle is not conducive to the im provement of the vortexcontrolled serpentine inlet performance. （2） Uplifting the lower wall of second Sduct properly could alleviate the adverse pressure gradient on the wall, which has positive effects on the flow within ducts. （3） While the design parameters are chosen ap propriately, the totalpressure recovery coefficient of the vortexcontrolled serpentine inlet is 0. 9667 under design conditions, the distortion index is 0. 245 1, and the inlet performance has been significantly improved.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第10期2355-2363,共9页
Journal of Aerospace Power
基金
国家自然科学基金(11002069)
