swept wing的例句大全

On a swept wing airplane, this effect is due to two causes.

在后掠翼飞机, 这种效果是由于两个原因.

Calculation of the Aerodynamic Interaction between Rotor/ Wing/ Fuselage of Tilt-Rotor; the sleek swept wings of the plane.

倾转旋翼飞行器旋翼/机翼/机身气动干扰计算飞机有后掠翼的圆滑的机翼。

Flow Control Technique for Forward-swept Wing Blended Body Tailless Configuration

前掠翼融合体无尾布局流动控制技术

This paper investigates a new flow control technique based on a forward-swept wing blended body ( FBB) tailless configuration by a wind tunnel.

通过风洞实验，研究了基于前掠翼融合体无尾气动布局的一种新概念流动控制技术。

numerical results of steady, compressible, lamina and turbulent boundary layers over the finite swept wing show to be satisfactory.

算例表明，能获得令人满意的三维机翼定常可压缩层、湍流边界层的计算结果。

numerical results of steady, compressible, lamina and turbulent boundary layers over the finite swept wing show to be satisfactory.

算例表明，能获得令人满意的三维机翼定常可压缩层、湍流边界层的计算结果。

Full 3D iterative solution of transonic flow for a swept wing test channel

后掠冀跨声流场S1/S2流面全三元迭代解

The Flow Characteristics and Its Melioration of Swept Wing/ Body Interference

后掠翼身干扰区流动特性及改善措施研究

A recording system of laser sheet visualization comprising laser source and CCD camera was employed for the visualization and real time recording to investigate the flow past a highly swept delta wing equipped with apex flap and leading edge flaps.

在低速实验中，应用激光片光源和CCD摄像系统，对一装有前端襟翼和前缘襟翼的双襟翼74°后掠三角翼进行实时记录与流态显示的试验技术和图像的三维重建。

A variant of the swept-back wing is the delta wing.

后掠翼的变型是三角翼.

The H-O grid is suggested in this paper to compute the compressible flow past highly swept slender wing-body combinations. Full-potential equation, finite difference method and approximate factorization iteration scheme are used.

用H－O网格、守恒型全位势方程、差分和隐式近似因式分解迭代算法计算绕大后掠细长翼－身组合体的可压缩流动。

The flow over delta wing with 65 ° and 70 ° swept at high angle of attack is investigated by solving the three dimensional, compressible Navier Stokes equations utilizing the second order upwind TVD algorithm ( Harten Yee).

采用Harten－Yee的二阶精度隐式TVD格式对N－S方程进行数值模拟，研究了后掠角为65°和70°的三角翼绕流的流场特性。

the more swept-back the wing angle, the less the drag and the better for flight approaching supersonic speed.

越是掠翼角，少的阻力和为接近超音速飞行更好。