大攻角,high angle of attack
1)high angle of attack大攻角
1.A measurement technique for derivatives of aircraft due toacceleration in heave and sideslip athigh angle of attack;飞行器大攻角升沉平移加速度导数测量技术
2.An application of the continuous scan technique to thehigh angle of attack fighter model test;大攻角连续扫描试验技术在某型号飞机上的应用
3.Analysis of supersonic flutter of the wing withhigh angle of attack with aerodynamics heating;气动加热环境下大攻角翼面超音速颤振分析
英文短句/例句
1.UNSTEADY AERODYNAMIC MODELING AND IDENTIFICATION OF AIRPLANE AT HIGH ANGLES OF ATTACK飞机大攻角非定常气动力建模与辨识
2.The Controller of Side Force of High Angles of Attack Based on LabWindows/ CVI;基于LabWindows/CVI的大攻角侧向力控制器
3.The Study on the Large Angle of Attack Scanning Characteristic of Asymmetric Terminal Sensing Submunition and Its Application非对称末敏子弹大攻角扫描特性研究及应用
4.Experimental Study on the Flow Patterns of a Simplified Aircraft Model at High Angles of Attack某型号飞机简化模型大攻角流态初步研究
5.A New Progress Applying Nonlinear Vortex Lattice Method to Tactical Missile at High Angles of Attack非线性涡格法应用于大攻角战术弹新进展
6.NUMERICAL SIMULATION OF SUPERSONIC SEPARATED FLOW OVER BLUNT CONES AT HIGH ANGLES OF ATTACK钝锥大攻角超声速分离流场的数值模拟
7.On the Position Machine Software Design of the Controller of Big αangle and Side Force;大攻角侧向力控制器的上位机软件设计
8.Optimum design for 2-D inlet while large AOA considered大攻角条件下的二维进气道型面优化设计
9.The Design for Autopilot of Large Attack Angle Missile by Using Feedback Linearization Method大攻角飞行导弹自动驾驶仪反馈线性化设计
10.Engineering Calculation Method for Supersonic Missile"s Axial Force in Large-Scale Attack/Deflection Angle大攻角/舵偏角条件下超声速导弹轴向力工程计算方法
11.However, there still are many problems in high-angle-of-attack to aircraft flight test data and use in aircraft design.然而，大攻角空气动力学仍然有许多问题需要加以解决。
12.Nonlinear Dynamic Stability Analysis for the Aircraft Flying at High Angles of Attack大攻角下有限振幅俯仰飞行的非线性动稳定性分析
13.Study on Asymmetry of Flow Around Slender Body of Revolution at High Incidence and Asymmetry Control Using Minute Jets细长旋成体大攻角绕流非对称性及其微型射流控制研究
14.Numerical Study of Combined Perturbation Control of Asymmetric Vortices on a Slender Body of Revolution at High Angle of Attack大攻角细长旋成体非对称涡组合扰动控制的数值研究
15.Primary Analysis of Vibration Aerodynamic on a Airfoil at High Attack翼型大攻角的振动对气动性能影响的初步分析(英文)
16.Numerical Simulation of Cruciform Missile at High Angle of Attack Based on N-S Equation基于N-S方程的十字翼大攻角导弹绕流数值模拟
17.angle of attack: 0, 4 and 8 deg;攻角0°,4~(?) ,8~(?)
18.Hexagon head tapping screw and big washer assembliesGB/T9074.23-1988六角头自攻螺钉和大垫圈组合件
相关短句/例句
large angle of attack大攻角
1.The static aerodynamic characteristics for slender bodies atlarge angle of attack was analyzed.研究分析了细长旋成体弹身类型气动外形的大攻角范围气动特性。
2.This kinetic model can be used in ballistic calculation of projectile withlarge angle of attack and also in the design of some .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。
3.Based on traditional bracing system of wind tunnel testing, a system of hanging brace oflarge angle of attack was designed, which can reduce frame interference.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。
3)large attack angle大攻角
1.The frequency of oscillating excitation has more effect on improving aerodynamic performance of airfoil atlarge attack angle th.利用振荡扰流进行了改善风力机翼型大攻角下性能的研究。
2.This paper presents a numerical simulation of separated flow over an airfoil atlarge attack angles with oscillating excitations to study separation flow control over an airfoil.为了研究大攻角下振荡射流控制翼型流动分离的机理,应用基于有限体积法和压力修正的SIMPLEC算法,数值模拟了表面施加振荡射流的翼型分离流动。
3.Based on the characteristics of the complicated aerodynamics for thelarge attack angle air-to-air missile,using feedback linearization approach for the design of the flight control system is proposed.针对大攻角空空导弹飞行过程中复杂的非线性空气动力学特性,提出了采用反馈线性化进行控制器设计的方法。
4)high angles of attack大攻角
1.Analysis of high speed Reynolds number effect tests athigh angles of attack;高速大攻角Re数效应试验与分析
2.The research of effect of flow turbulence on the aerodynamic characteristics of a wing body combination athigh angles of attack;湍流度对翼身组合体大攻角气动特性的影响研究
3.This paper describes a wind tunnel free-flight technique for measuring pitch-damping derivatives of a missile model athigh angles of attack.实验时用气体发射装置将模型向实验段上游发射;并以另一气流横吹模型使其呈大攻角状态飞行。
5)high incidence大攻角
1.Analysis of the unsteady character of the flow field athigh incidence;大攻角流动的非定常特性分析
2.Investigation of pneumatic characteristics for a ventral S-shaped inlet athigh incidence and low speed;一种腹下S弯进气道低速大攻角下气动特性实验
3.The process of primary vortices forming,lifting and shedding alternately along central axis from opposite sides of a slender body placed athigh incidence to an oncoming stream is investigated numerically,and laws on axial evolution of its sectional flow-pattern topological structure are advanced.运用数值方法研究了细长体大攻角绕流背风面两侧主涡沿轴向交替形成、飘起、脱落的过程,提出了绕流截面流态拓扑结构的轴向演化规律,详细描述了主涡诱导产生二次涡、二次涡分割主涡衍生出tertiary涡、主涡与异侧二次涡绕合、主涡分割异侧主涡形成脱体涡等现象,突出了二次涡、tertiary涡的作用。
6)maximal attack angle最大攻角
1.At the same time, the effects of the Strouhal number andmaximal attack angle on the hydrodynamics performance of the flexible fin were analyzed.同时计算分析了斯特劳哈尔数、最大攻角等参数对柔性鳍水动力性能的影响,建立了最大推力系数和最高推进效率所对应的参数区间,其中低St数的最高推进效率发生在低αmax,高St数的最高推进效率发生在高αmax。
延伸阅读
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