airfoil wake flow

基本解释

Boundary-layer, surface pressure, wake velocity measurements and flow visualization are tested for different configurations of multi-element airfoil.
对具有襟翼不同缝道构形的多段翼型进行了翼面边界层、表面压力、尾迹速度的测量，同时作了翼面流谱观察实验。
Detailed 2D velocity and vorticity fields were measured to investigate the turbulent near wake flow of NACA0012 airfoil with on-line cross-correlation PIV in low-speed wind tunnel.
利用在线式互相关PIV系统，在低速风洞中对NACA0012翼型的近尾迹流动进行了实验研究。
Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions.
在亚跨声速时分别采用了表面积分和尾迹积分求得给定翼型RAE2822的阻力。