1) isolated wing
弧立机翼
2) lower camber side
机翼下弧面
3) circular arc wing
圆弧形机翼
4) airfoil with cubic nonlinearity
立方非线性机翼
1.
The Limit Cycle Oscillation (LCO), bifurcation and flutter of the airfoil with cubic nonlinearity are investigated.
研究超声速及高超声速流中立方非线性机翼的极限环振荡(LCO)、分岔及颤振。
5) Wrap around fins
卷弧翼
1.
In the paper,aerodynamic characteristics of a missile with abnormity wrap around fins is computed by CFD method,and the curves of axial force coefficient,normal force coefficient,lateral force coefficient,roll moment coefficient,yaw moment coefficient and pitch moment coefficient is plotted.
采用CFD方法计算了一种异形卷弧翼弹的气动特性,得出了轴向力系数、法向力系数、横向力系数、滚动力矩系数、偏航力矩系数和俯仰力矩系数曲线,所计算的系数可以用于弹的外形结构设计和弹道仿真。
2.
A zero-install roll angle of the wrap around fins projectile still has roll moment at zero angle of attack.
卷弧翼是其中一种比较方便的方法。
6) wrap-around fin
弧形翼
1.
Numerical study is conducted to investigate wrap-around fin(WAF) at supersonic and hypersonic Mach number(M_∞∈\).
5)范围内进行了弧形翼的数值研究,主要分析了弧形翼在零攻角下产生升力的原因,并且研究了弧形翼曲率对升力的影响。
2.
The flowfield of projectile with wrap-around fins was numerically investigated at supersonic Mach numbers(1.
通过有限体积法和二阶迎风格式,对弧形翼-身组合体流场进行了数值仿真研究。
3.
Spalart-Allmaras turbulent model is used for the numerical simulation of projectile configuration with four wrap-around fins in supersonic speed.
数值模拟结果给出了弧形翼附近的流场结构,并对弧形翼凹凸表面的压力分布做了详细分析,得出了弧形翼在零攻角下产生升力的机理。
补充资料：安立谛非安立谛
【安立谛非安立谛】
（术语）述记十九曰：“有差别名言者名安立，无差别离名言者，非安立也。安立者施设义。”
（术语）述记十九曰：“有差别名言者名安立，无差别离名言者，非安立也。安立者施设义。”
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