1) leading-edge extension (LEX)
前缘翼根延伸
1.
To enhance the maneuverability of the selected aircraft model, a standard genetic algorithm (GA) is used as an optimization method for the preliminary design of the leading-edge extension (LEX) layout.
为了提高所选定飞行器模型的机动性,采用了一种标准遗传算法设计前缘翼根延伸(LEX)。
2) front wing extension panel
前翼板延伸板
4) sharp fin
尖前缘翼
1.
This paper presents the distributions of wall pressure and heating rate on the flat plate and fin surface for 20°,30° and 35°un-swept sharp fins at freestream Mach numbers of 7.
4×10 ̄7/m气流绕迎角为20°、30°和35°尖前缘翼运动时,平板锥型干扰区的壁面压力和热流率分布。
2.
This paper presents the surface characteristics of the inter-action between shock wave and turbulent boundary layer induced by sharp fin with emphasis on Mach number effects.
本文介绍了尖前缘翼诱导激波和湍流边界层干扰流场壁面特性,着重强调马赫数影响。
5) leading edge slat
前缘缝翼
6) wing leading edge
弹翼前缘
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