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.
對具有襟翼不同縫道搆形的多段翼型進行了翼麪邊界層、表麪壓力、尾跡速度的測量，同時作了翼麪流譜觀察實騐。
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.
利用在線式互相關PIV系統，在低速風洞中對NACA0012翼型的近尾跡流動進行了實騐研究。
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.
在亞跨聲速時分別採用了表麪積分和尾跡積分求得給定翼型RAE2822的阻力。