airfoil wake flow

基本解釋

Boundary-layer, surface pressure, wake velocity measurements and flow visualization are tested for different configurations of multi-element airfoil.
對(duì)具有襟翼不同縫道搆形的多段翼型進(jìn)行了翼麪邊界層、表麪壓力、尾跡速度的測(cè)量，同時(shí)作了翼麪流譜觀察實(shí)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(guān)PIV系統(tǒng)，在低速風(fēng)洞中對(duì)NACA0012翼型的近尾跡流動(dòng)進(jìn)行了實(shí)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(shí)分別採(cǎi)用了表麪積分和尾跡積分求得給定翼型RAE2822的阻力。