1) infinite swept wing
无限展长后掠翼
1.
In order to achieve the fluid field of an "Infinite Swept Wing" in a wind tunnel,wall-liners formed from the inviscid streamlines of an infinite swept wing are designed to correct the side wall influence of the wind tunnel.
在风洞实验中,为了获得一个近似无限展长后掠翼的三维流场实验条件,必须采用特殊的整流措施,修正洞壁对流场的干扰。
2.
Then the chord-wise amplification rates of cross-flow wave with different wavelength can be calculated and the most amplification stationary wavelength can be determined for an infinite swept wing.
采用Mack方法求解忽略曲率和压缩性的三维线化稳定性方程(Orr-Sommerfeld方程),针对无限展长后掠翼,计算分析边界层内不同波长横流驻波沿弦向的放大率,确定最不稳定波的波长。
2) sweep wing
后掠翼
1.
Influence of sweep wings on side force of forebody of a slender;
后掠翼对细长体头部侧向力特性的影响
2.
Influence on flow around mid-part of slender at high AOA by sweep wing;
后掠翼对细长体中段大迎角绕流的影响
3) sweepback tail
后掠尾翼
4) swept-back wing
后掠翼<火>
5) swept wing
后掠翼
1.
Transition studies for the boundary layer on a swept wing based on sublimation technique
基于升华法实验研究后掠翼三维边界层的转捩
2.
This paper reports the measurement of transition location change of NLF(2)-0415 swept wing in a low-speed flow along with the attack angle based on sublimation method in a low turbulence wind tunnel mounted at Northwestern Polytechnical University.
报导了在西北工业大学低湍流度风洞中采用升华法测量后掠翼上表面流动转捩位置及其随攻角变化而改变情况,并参照后掠翼压力分布的实验结果进行分析。
6) high-aspect ratio sweepback wing
大展弦比后掠机翼
1.
Coupled with 3-D ALE Euler solver this dynamic unstructured grid method is applied to simulating transonic unsteady flow about a rectangle rigid wing and a high-aspect ratio sweepback wing.
应用本文发展的非结构动网格生成方法并通过耦合求解基于ALE(Arbitrary Lagrangian-Eulerian)描述的Euler方程,模拟了做谐和振动的矩形刚性机翼及大展弦比后掠机翼弯扭耦合振动跨音速非定常绕流,计算结果与参考文献提供的结果及实验结果吻合良好。
补充资料：变后掠翼飞机(见后掠翼飞机)
变后掠翼飞机(见后掠翼飞机)
swing-wing aircraft
bianhoul位eyi feiii变后掠翼飞机(swing一wing aircran)见后掠翼飞机。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条