后掠翼

在贝尔X-5和空军赋予的NACA研究人员一个机会来测试可变后掠翼。

The Bell X-5 gave NACA and Air Force researchers a chance to test out variable-sweep wings .

文中给出了矩形翼和后掠翼定常和非定常气动载荷的数值结果，其精度数值与DLM的相当，计算效率提高一倍。

Numerical results of the steady and the unsteady aerodynamic loading are given for rectangular wings and swept-back wings , the numerical exactness is equivalent to DLM , the calculating efficiency of DPM is twice as large as DLM .

所以从70年代中期开始，伊朗成为了除美国之外唯一一个拥有最强大截击机的国家，即格鲁曼F14雄猫战机，这是一款可变后掠翼舰载机，装备有复杂的雷达和长程AIM54凤凰空空导弹。

That 's how , starting in the mid-1970s , Iran became the only country besides the United States to operate arguably themost powerful interceptor jet ever built ? - ? the GrummanF-14 Tomcat , a swing-wing carrier fighter packing a sophisticated radar andlong-range AIM-54 Phoenix air-to-air missiles .

后掠翼的变型是三角翼。

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

后掠翼身干扰区流动特性及改善措施研究

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

侧滑对后掠翼飞机俯仰操纵影响的探讨

The effect of sideslip on longitudinal control of sweptwing aircraft

后掠翼身干扰区流动显示

Display Flow Visualization of Swept Wing / Body Junctions

后掠翼对细长体中段大迎角绕流的影响

Influence on flow around mid-part of slender at high AOA by sweep wing

底部喷流及后掠翼前缘涡破碎的流动显示研究

Flow Visualization of Base Jet and Vortices Breakdown at Leading-edge of a Swept-back Wing

飞机有后掠翼的圆滑的机翼。

The sleek swept wings of the plane .

基于升华法实验研究后掠翼三维边界层的转捩

Transition studies for the boundary layer on a swept wing based on sublimation technique

基于线化稳定性理论的后掠翼边界层内横流稳定性研究

Study on Crossflow Instability of Boundary Layer on a Swept Wing based on Linear Stability Theory

主翼襟翼液压执行机构后掠翼人工诱导横流驻波的升华法研究

Main foil flap hydraulic actuator Sublimation investigation of artificial abduction crossflow stationary wave in swept wing

研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响。

The influence on flow structure and aerodynamic of a slender by sweep wing at high angle of attack was studied .

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。

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

本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。

The unsteady flow field near the leading edge of an oscillating sweptback wing is obtained by using 3-D subsonic lifting surface theory .

本文提出一种确定跨音速后掠翼抖振边界的数值计算方法，现有的确定跨音速翼型抖振边界的F。

A numerical computational method has been developed to predict the buffet boundaries of swept wings in the transonic flow regime . The existing criterion of F.

用适当的坐标变换把后掠翼变成矩形翼，再把无限物理空间变成有限的计算空间。

The infinite physical domain is transformed to the finite computing domain and the swept wing is transformed to the rectangle wing , using proper mathematical transformation .

这种方法不需要计算出无粘流线的细节，并适用于不同外形的后掠翼。

The method does not require to calculate the details of the stream lines and can be used for various swept wings at moderate angle of attack or yaw angle .

实验结果表明，在30°迎角时，细长体中段背风侧的流动和压力分布受到后掠翼与头部背涡的双重控制。

The experimental results indicate that at angle of attack 30 °, the flow and pressure distribution of mid-part leeside of a slender are dominated by sweep wing and forebody vortices .

本文以大展弦比、后掠翼飞机和轴对称导弹为例，分别建立了弹性飞机和细长体弹性飞行器在大气紊流中飞行时的动力学模型。

In this paper , a dynamic model of elastic vehicles flying in atmospheric turbulence is presented , which is based on large aspect ratio , sweptback wing airplane and axis symmetrical missile respectively .

对后掠翼、前掠翼和翼身组合体等算例的计算表明，计算结果的准确度与高阶面元法相近。

Illustrative calculations for several test cases such as swept back wing , swept forward wing and wing-body combination show that the accuracy of re-sults may be improved and is competitive with high-order panel method .

大后掠翼前缘涡对其颤振特性的影响主机翼前掠角较小时，鸭翼改善和提高升阻比的效果比较明显。

Effects of Leading-edge Vortex on Flutter Characteristics of High Sweep Angle Wing Much more increase of maximum lift-to-drag ratio can be obtained with a forward-swept main wing with a small sweepback angle leading edge .

计算表明，前掠翼比后掠翼更接近最佳载荷分布，应用跨超音速面积律计算有鸭翼的前掠翼组合体，其轴向截面分布较易接近最佳当量分布，因而零升波阻显著减小。

According to the area rule computation , the area distribution of FSW is easier to approach the optimum form than that of ASW . The configuration with FSW thus leads to an apparent reduction of the wave drag .

激波掠过后岩石相对损伤度与裂缝渗透率关系模拟实验研究后掠翼人工诱导横流驻波的升华法研究

Simulation research on relationship between relative damage of rock and fracture permeability after exploding wave bypassing