超临界机翼

对LockheedC-5A机翼和F-8超临界机翼给出了一系列计算结果，并同其它方法的结果以及试验数据作了比较。

Several computational results for Lockheed C-5A aircraft wing and F-8 supercritical wing are given in the paper , and comparisons with other methods and with experimental data are made as far as possible .

转捩对超临界机翼压力分布的影响分析

Investigation of transition effect on the pressure distribution of supercritical wing

超临界机翼飞行验证机的增升装置设计

High Lift System Design for a Supercritical Wing Flight Test Plane

超临界机翼静气动弹性特性研究

An Analysis Method of Static Aeroelastic Characteristics of Supercritical Wing

超临界机翼气动设计的准则、流程和设计实例

Aerodynamic design criteria , design procedures and a design example of supercritical wing

超临界机翼&尾吊短舱布局高速气动综合研究

A Study on High-Speed Aerodynamic Intergration of the Supercritical Wing and Rear-Mounted Nacelle Configuration

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

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

计算表明，短舱、挂架对超临界机翼的气动特性有显著的影响。

Results of the calculation show that pylon and nacelle have significant effect on the supercritical wing aerodynamic characteristics .

研究结果表明，微型梯形涡流发生器对超临界机翼附面层分离的控制主要起减阻作用；

The results indicate that the principal effect of micro-trapezoid vortex generator is drag saving for boundary layer separation control of supercritical wing .

为进行超临界机翼气动设计技术的飞行验证，将某教练机改装为飞行验证机，为此必须进行增升装置的重新设计。

In order to validate the philosophy and software of supercritical wing design , a training plane is refitted and its high lift system is redesigned .

超临界层流机翼边界层及气动特性分析

Analysis of the Boundary Layer and Aerodynamic Characteristics of a Supercritical Laminar Wing

本文在微型涡流发生器控制超临界翼型附面层分离实验研究的基础上，在低速风洞中研究了微型涡流发生器弦向位置和安装偏角对超临界机翼附面层分离控制效果的影响。

This paper investigates the effect of the chordwise position of microvortex generators and their installation angles on the boundary layer separation control for supercritical wing in the low speed wind tunnel .