三角翼匀速上仰跨声速非定常流场数值模拟  

Numerical Simulation of Unsteady Transonic Flows Around a Pitching Delta Wing

作　　者：周伟江[1] 李锋[1] 马汉东[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《空气动力学学报》1997年第1期108-113,共6页Acta Aerodynamica Sinica

摘　　要：用有限差分法求解N－S方程，数值模拟了细长三角翼作匀速上仰运动时的跨声速绕流流场。给出了非定常流场结构，涡破裂特性和非定常升力、阻力特性，研究了上仰运动对动态失速的影响。The unsteady transonic flows around a pitching slender delta wing are simulated numerically with solving unsteady compressible Navier-Stokes equations by implicit finite difference TVD scheme. The unsteady flowfield structures, the features of vortex-breakdown and the characteristics of unsteady lift/drag are presented. The effect of pitching movement of the wing on dynamic stall is also studied.

关 键 词：跨声速绕流 非定常流 涡破裂 数值模拟 三角翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]