测量攻角具有十分重要的意义。
提出了一种新的测量弹丸攻角的方法。
A new measurement method for nutation Angle has been put forward.
如上所述，设计攻角的第二部分是10甘醇。
As seen above the design Angle of attack for the second segment is10deg.
如上所述，设计攻角的第二部分是10甘醇。
As seen above, the design Angle of attack for the second segment is10 deg.
实验是在不同的攻角和不同的密流比下进行的。
The experiments are carried out with different incident angles and blowing ratios.
攻角随增加的速度。
这种情形会发生于飞行伞的翼负载相当于攻角时。
This occurs at one angle of attack for the same wing loading of a paraglider.
探讨了水翼瞬时攻角、及柔度对摆动水翼推进性能的影响。
The influence of the instantaneous angle of attack and ST on the performance of propulsion is investigated.
飞机于就是进入了中度攻角的过载滚转并向右后方向掉落。
The jet goes right into the medium AOA loaded roll and just flops right back around.
当我们遇到暂时性上升空气时，飞行伞会随著攻角增加而上升。
When confronted momentarily with an ascending air current, the paraglider climbs since the Angle of attack has increased.
得到标枪的初始攻角和俯仰角速度对出手角度选择的影响较显著。
The effect of initial attack angle and pitching angular velocity on the selection of release angle is remarkable.
这两个部分是独一无二的，专为开发成效最大，在低速和高攻角。
Both these sections are unique and developed specifically for maximum effectiveness at low speeds and at high angles of attack.
在零攻角实验时不同模型的空气动力阻力是采用简化方法来计算的；
The aerodynamic drag of different models at zero angle of attack in the experiment is calculated using the simplified procedure.
因此对它的求解，要较相应另攻角轴对称绕流的二点边值问题简便。
Therefore, the solutions can be obtained more easily than that of two point boundary value problems of axisymmetric flow case.
使用符号运算方法设计了系统闭环控制律和大攻角下的过失速控制律。
The control laws of the inner closed loop system and post stall maneuver are obtained through using symbol operations design.
当物体离壁面很近时，出现排斥现象，水动力系数随攻角的变化呈非线性特征。
While for small clearance, there appear repulsion phenomena, and the variation of coefficients with attack Angle is nonlinear.
本文研究平面强爆震波对静止的零攻角二维对称薄翼的绕射问题，并求得解析解。
An analytical solution is obtained for the diffraction of strong detonation waves by a stationary two-dimensional thin airfoil.
基于传统的风洞试验支撑系统，设计了能减小支架干扰的大攻角张线式支撑系统。
Based on traditional bracing system of wind tunnel testing, a system of hanging brace of large Angle of attack was designed, which can reduce frame interference.
我要在同一时间注意观察下降率，高度，空速，攻角，还有我的驾驶杆杆位和油门。
I have to monitor sink rate, altitude, airspeed, AOA, and my stick and my throttle all at the same time.
提出应用线阵CCD技术测量飞行弹丸攻角，建立了测量飞行弹丸攻角的计算方法。
In the paper, a method is developed about attack Angle measurement of flying projectile with linear array CCD technology, and the calculation method of the attack Angle established.
在飞行时，当伞翼变的极度容易折湾及崩溃时，攻角只能被调整至一个非常小的角度。
In flight, the Angle of attack can only be adjusted to a small degree, as the wing is highly pliable and subject to collapse.
本文概述最初阶段利用风洞试验数据应用模糊逻辑研究飞机大攻角空气动力学的情况。
In this paper, the initial stage in application of fuzzy logic to aircraft high-Angle-of attack aerodynamics using wind tunnel test data is outlined.
给出了两种控制方法的导引律，计算了典型弹道的攻角、俯仰角和交班点速度等参数。
The Angle of attack, pitch Angle and velocity at shifted point for typical trajectory were calculated.
此动力学模型可用于弹丸大攻角飞行时的弹道计算及某些灵巧弹药（如末敏弹）的设计。
This kinetic model can be used in ballistic calculation of projectile with large angle of attack and also in the design of some smart munitions(e. g. target sensitivity projectile).
本文应用零方程模型和二方程模型计算了椭球体有攻角绕流对称面上的三维湍流边界层。
Revised method is proposed for calculation of three dimensional turbulent boundary layers on the surface of symmetry plane of a flow around ellipsoid at incidence.
结论是：提高大攻角实验数据准确度的关键在于减少和修正由于阻塞效应引起的系统误差。
The conclusion is that the key to raise the experimental accuracy lies in reducing and correcting the systematic errors due to blockage effect at high angles of attack.
我让飞机完成整个的大回环动作，并且检查这个时候的高度、空速还有攻角，准备做过载滚转。
I fly the jet out of the loop, and I look to catch the right altitude, airspeed, and AOA for the loaded roll.
基于传统的风洞试验支撑设备，设计了用于低速风洞测量大攻角模型支架干扰的组合支撑设备。
Based on traditional support system in wind tunnel testing, the combination support system measuring support interference on high angles of attack model in low speed wind tunnel was designed.
尾部设计：甲烷的短距起降801尾节的目的是提供在高攻角的最大效益（控制）的速度和缓慢。
TAIL DESIGN : The STOL CH 801 tail sections are designed to provide maximum effectiveness (control) at slow speeds and at high angles of attack.
在实际弹丸飞行姿态测试试验中，该测试系统可以较好的完成实时测试小弹丸攻角和速度参数的任务。
In the experiment for measuring bullet attitude, this measurement system can accomplish real-time measuring small bullet Angle of attack and velocity parameter.
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