Supercritical airfoil

Experimental Investigation into Effects of Gurney Flaps on Supercritical Airfoil

超临界翼型Gurney襟翼增升实验研究

The Investigation of the Effect of Airfoil Modification on the Aerodynamic Performance of Supercritical Airfoil

翼型改型对超临界翼型气动性能影响的研究

Investigation of boundary layer separation control for supercritical airfoil using micro vortex generator

微型涡流发生器控制超临界翼型边界层分离实验研究

Simulation of Transonic Slot Wall Interference on Supercritical Airfoil Using N-S Equation

跨声速开槽壁超临界翼型洞壁干扰的N－S方程模拟

Rapid Modeling of a Supercritical Airfoil ′ s Integral Wing Plane Panels Based on Feature Mapping

基于特征映射的超临界机翼整体壁板板坯快速建模技术研究

The paper investigates the problem on vortex generator control boundary layer 's separation of supercritical airfoil and wing for body configuration wing .

本文研究涡流发生器控制超临界翼型和翼身组合体机翼的附面层分离问题。

An experimental study was performed on a supercritical airfoil in the FL 21 wind tunnel to investigate the lift enhancement effects of the Gurney flaps at high speed conditions .

在FL21风洞中进行了高速情况下Gurney襟翼对超临界翼型增升实验研究。

For a given Mach number and incidence , the calculated pressure distribution on the airfoil having porous regions , is used to generate the contour of an equivalent solid airfoil whose shape resembles that of an supercritical airfoil .

给定M数和迎角时，可利用计算的多孔翼型的压力分布，来产生外形类似于超临界翼型的实心翼型的压力分布。

According to the character of boundary layer separation of the supercritical aerofoil , the flow mechanism of micro vortex generator and the flow separation control effectiveness of the different trapezoid vortex generator height and chordwise position on the supercritical airfoil has been studied .

根据超临界翼型边界层分离特性，提出了涡流发生器的流动机理。研究了梯形涡流发生器不同高度和弦向位置对边界层分离控制效果的影响。