查询词典 angle of attack

For gas flow past cylinder, the characters of flow field in different Mach number and Knudsen number condition were investigated, and especially for low Knudsen number cases, the results were compared with calculating results of Euler's equation. It showed that they are correspondent by comparing the characters of bow shock and wake. The convergence rates of different high resolution and implicit schemes were also investigated. The convergence behavior of the implicit WENO scheme developed in this paper is better than others. For gas flow past NACA 0012 airfoil, the calculating results were compared with results of experiment. It showed that the results of WENO scheme are of higher accuracy for the case with angle of attack.

在圆柱流场时，我们探讨不同马赫数且不同纽森数时的流场特性，并在低纽森数时，与那维尔-史托克方程式的计算结果比较，我们比较了弓形震波及尾流附近的特性，其结果是相当符合的，同时我们也比较不同高解析隐式算则的收敛历程，从收敛历程图可得到，本文发展出来的隐式WENO算则有较佳的收敛效果；在NACA 0012翼形的流场中，我们将与实验结果做比较，发现利用WENO算则计算的结果，对於具有攻角的流场，亦有相当高的准确度。

Dynamic derivatives of a 60° delta wing and F-18 aircraft model are calculated by this method, and then the effects of the amplitude,the frequency and the change of angle of attack on the dynamic derivatives are studied.

对60°三角翼和F-18飞机模型进行动导数仿真计算，研究了不同振幅、频率及迎角变化对动导数的影响。

Within the field of ground effect, aerodynamic forces of the wing-in-surface effect crafts are not only decided by the angle of attack, but also by the flying height, and they lead to more complicated stability problems.

在地效作用区域内，地效飞机的气动力不仅与迎角有关，而且与飞行高度有关，因而其飞行稳定性问题更为复杂。

The boundary layer edge conditions and the resistance and lift force coefficient in different Mach number and different angle of attack are worked out. Results of the method are in good agreement with the aerodynamics rules.

从而得到了边界层的外缘参数，计算出了弹丸在不同马赫数和不同攻角下的阻力系数和升力系数，分析结果符合空气动力学的基本规律。

Then, in the viscous fields, based on reference enthalpy theory and semi-empirical formulas, using the boundary layer edge conditions and classic methods, calculated the heating rates and the temperature on the heads of projectile in different Mach number and different angle of attack.

在粘性主导区内，在理论与半经验公式的基础上，利用参考焓方法，将无粘数值求解得到的边界层外缘参数代入经典的热流计算公式，从而得到不同马赫数、不同攻角时弹丸头部的表面热流和温度。

Complex wave structures of supersonic inlet at different inflow Mach number and angle of attack related to critical status were achieved by numerical simulation.

通过数值模拟得到了对应于不同来流马赫数和攻角情况下，临界工况时，超声速进气道内外粘性流场复杂的波系结构。

Wind tunnel investigation is conducted on six different canard configuration models over range of Mach from 0.8 to 2.5.The experiment data analyzes the regulation of rolling characteristics with Mach number and angle of attack,and the effect of rolling characteristics for different configurations is discussed.The rolling damping characteristics are also studied.

通过风洞实验得到了跨、超音速下六种组合模型的气动力数据，由实验结果分析了远程弹滚转特性随马赫数和攻角的变化规律，以及不同鸭式气动布局对滚转特性的影响，此外还分析了远程弹的滚转阻尼特性。

In this paper, the direct simulation Monte Carlo method is employed to simulate flows of modeled air vehicles having simple geometric shape such as delta wing at a Knudsen number between 0.001 and 0.1 for various Mach number and angle of attack conditions. With the calculated aerodynamic forces and heating, we obtained the general behavior of the rarefied gas effects on the vehicles' aerodynamics.

本文采用直接模拟 Monte Carlo 方法，模拟了简单外型如三角翼形的模型飞行器在努森数为 0.001到 0.1的范围内以不同来流马赫数和不同飞行攻角飞行时的流场，计算了飞行器所受到的气动力和气动热，获得了稀薄气体效应对飞行器气动性能影响的一般规律。

The purpose of the present paper is to investigate the characteristic feature of the aerodynamics of a nose cone at a high angle of attack and study the vortex stability problem for the flow over a flat-plate delta wing with the dorsal fin .

本论文主要是通过实验来研究细长圆锥体在大迎角下的绕流流场的特性和细长三角翼加背鳍后对前缘涡的影响，检验相关理论结果。

Firstly, stability of a hypersonic boundary layer on a blunt cone with small nose bluntness at zero angle of attack has been investigated and the transition location was predicted by the e-N method.

本文研究零攻角和小攻角、超音速和高超音速、尖锥和小钝头锥边界层的转捩预测问题。

But we don't care about Battlegrounds.

但我们并不在乎沙场中的显露。

Ah! don't mention it, the butcher's shop is a horror.

啊！不用提了。提到肉，真是糟透了。