攻角

运用Fourier函数分析法逼近大攻角非定常气动力阶跃响应模型。

A nonlinear unsteady indicial response model of aerodynamic coefficient could be approximated by the use of Fourier analysis function at high angle of attack .

以求解二维N-S方程数值模拟NACA0012翼型大攻角状态的可压绕流特性；N-S方程是在贴体坐标系中给出的，以代数方法生成C型网格系统。

Compressible flow around an NACA 0012 airfoil at high angle of attack is numerically simulated by solving the two-dimensional Navier-Stokes equations in a body-fitted system , the grid system is C-type grid generated algebraically .

一种基于INS的攻角和侧滑角测量算法

An Estimation Method of Angle-of-attack and Sideslip Angle Based on INS

基于N-S方程的十字翼大攻角导弹绕流数值模拟

Numerical Simulation of Cruciform Missile at High Angle of Attack Based on N-S Equation

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 .

k-ωSST湍流模型与单方程的SA模型被结合使用，以适应大攻角范围翼型绕流的数值模拟。

K - ω SST turbulence model is combined with SA model to adapt to the numerical simulation of flow around airfoil in large attack angle range .

随着初始风攻角的加大，桥梁的稳定性降低。（3）运用MATLAB软件，采用谐波合成法与修正逆傅里叶变换法模拟了桥梁的脉动风场。

With the increase of the initial attack Angle , reduced stability of Bridges . ( 3 ) Adopts MATLAB software , using spectral representation and fixed inverse Fourier transform method simulate fluctuating wind field of bridge .

为了进一步揭示这一复杂流动现象的特性和物理模型，该文应用激光Doppler测速仪和七孔气动探针对一环形压气机叶栅在大攻角下的流道内部和流道出口的流场进行了实验研究。

In order to understand the characteristics of this complicated phenomenon , a strongly separated flow in an annular compressor cascade at large incidence was investigated using Laser Doppler Velocimeter ( LDV ) and 7 hole pneumatic probe .

2m和0.6m高速风洞飞机大攻角测力试验数据相关性研究M

Correlation study on force test data for aircraft at high angles of attack in 1.2m and 0.6m high speed wind tunnels

通过CFD模拟发现，具有后加载造型、相对厚度大于40%的翼型压力面出现明显分离，造成翼型小攻角失速、升力系数下降。

Turbulent separation occurs on pressure surface at small attack angles for the airfoils which relative thickness more than 40 % , making airfoil stall at small attack angles and the lift coefficient decrease .

c.攻角、喷流压比、喷流马赫数、来流边界层状态等内、外流参数变化对横向喷流干扰效应的影响分析。

Finally , the qualitative and quantitative effect of parameters such as attack angle , pressure ratio of jet , Mach number of jet and state of boundary layer on lateral jet interaction are analyzed in detail .

本文利用二维PIV技术研究了大正攻角情况下直、弯平面扩压叶栅内的内部流动结构。

This thesis presents a research on the flowfield of compressor cascades under large positive attack angles via PIV . The cascades are composed of conventional straight blades and positive curved blades .

应用三自由度强迫振动装置，解决了大攻角下弹性悬挂自由振动时存在的竖向运动失真问题，准确识别了大攻角下的H型和矩形断面杆件气动导数。

The forced vibration equipment with three degrees of freedom is applied to solve the distortion problem of vertical motion in free elastic suspension method , and the flutter derivatives of H-shaped and rectangular sections under large attack angle are accurately identified from the forced vibration testing data .

采用自制的动态旋转冲刷腐蚀装置，以含硅湿法磷酸为液固冲刷腐蚀介质，考察了该流动体系中316L和904L不锈钢在不同攻角下冲刷腐蚀的行为。

Behavior of erosion-corrosion in a slurry of wet process phosphoric acid containing SO 2 particales have been studied with different impact for 316L and 904L stainless steels using rotating method test apparatus .

采用控制容积积分法及压力修正算法，结合κ-ε湍流模型求解二维稳态雷诺时均N-S方程组，对一透平动叶栅在不同负攻角条件下的分离流动进行了数值模拟。

Finite volume approach and pressure-correct method are applied to numerically solve two-dimensional steady time-average N-S equations closed with κ - ε turbulence model and the separation flow in a turbine last stage rotor cascade at different negative incidence are simulated .

从纹影照片与横截面上的蒸汽屏照片对照可获得机翼锥面激波位置随Mach数的变化；以及激波－诱导分离线位置随Mach数和攻角变化曲线。

The variations of both the bow shock positions at different Mach numbers and the positions of separating lines induced by shock waves with Mach numbers and angles of attack are obtained based upon the schlieren plus the vapor screen photos in the sections .

在对NACAOO系列零攻角绕流计算中，比较了几种插值方法的影响。

In the calculation of the NACAOO series with zero attack , comparison is carried out for some interpolation methods .

在传统的流场测试手段&多孔探针结合压力扫描阀的测压方法和热线风速仪等的流场校测的基础上，采用PIV方法对风速均匀性和风攻角等进行了校测。

Based on the traditional flow field validation , which is the combination of pressure measuring method using parallel pitot tube plus pressure scanner system and velocity measurement method using hot wire anemometer , the velocity uniformity and wind attack angle are checked using PIV method .

应用强迫振动装置上的天平测量节段模型的气动力时程曲线，实现了随攻角连续变化三分力系数的测量，并由升力时程曲线推算了多组H型和矩形断面的Strouhal数。

The aerodynamic forces of section model are measured by the force balance of forced vibration equipment , which is further used to estimate the Strouhal number of H-shaped and rectangular sections , and the measurements of steady aerodynamic force coefficient continuously varying with attack angles are realized .

研究结果表明：在中心线起爆与端面起爆方式下的MEFP均能形成初速大、攻角小、气动性能良好的EFP。

The result indicates that it have the high elementary invite 、 the small angle of attack and well pneumatic steady shape of EFP in the MEFP warhead with the centre line detonation and the plane detonation .

旋成体零攻角纵向大扰动势流的AF-2迭代及其并行算法

AF 2 iteration and its parallel algorithm for transonic flow with large disturbances in freestream-direction around axisymmetric bodies at zero angle of attack

应用BaldwinLomax湍流二层代数模型模拟了大攻角时前缘分离涡的形成，旋涡对流及其非定常现象。

By using the Baldwin-Lomax turbulent model , the formation of the leading edge separation bubble , as well as the convection of vortex along the airfoil surface and unsteady phenomena of vortex are simulated at high angle of attack .

首先，研究了高超音速零攻角小球头锥边界层的稳定性特点，并用e-N法进行了转捩预测。

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 .

介绍了1.2m风洞攻角达30°的动导数试验装置与测量系统以及在1.2m风洞中对标准动态模型（SDM模型）所作的一系列试验结果。

In this paper , the test mechanism of dynamic stability derivative with angle of attack up to 30 ° and its measuring system are presented together with typical test results of a Standard Dynamic Model ( SDM ) in 1.2m transonic wind tunnel .

在实际应用中，根据试验需要，提出了基于PCI-1711采集卡的连续变攻角的控制方案，并且成功应用于型号试验，为我国重点型号飞行器的研制提供了可靠的试验平台。

The control project of continuum changing attack angle , which is based on PCI-1711 data collection card , has succeeded in applying model test and offered reliable test platform for development of important aircraft .

在二维零攻角来流情况下，考虑了两种流动状况，一种是完全层流无转捩；另一种为采用Batt边界层转捩准则来确定边界层转捩点。

There are two states to be considered here . One is the complete laminar boundary layer and the other is the boundary layer transition . The transition point is confirmed by Batt boundary layer transition criteria .

水洞实验中，来流速度为20cms、粗糙高度为0.8mm时流态随攻角的变化规律可用来解释风洞实验结果中力矩曲线的分散性。

In this water tunnel experiments , the results obtained at 20 ? cm / s for the roughness height 0.8 ? mm can be used to explained the scatter of the pitching moment curves obtained in the wind tunnel measurements .

数值模拟了流场的变化特征，分析了各种攻角下，具有方形截面的高层建筑的升力系数、抗力系数和Strouhal数。

The present discrete vortex model combined with singularity method can be easily applied to a building with complicated shape . The characteristics of wind field are numerically simulated , the lift and drag coefficients and Strouhal numbers are analyzed for several angles of attack .

采用微分形式的动力学方程和积分形式的运动学方程相结合的有效方法，以及可用于有分离流动的Baldwin-Lomax湍流模型，精确地模拟大雷诺数大攻角下的复杂流场。

The copulation of kinetic equation in terms of differential form and kinematic equation in terms of integral forms , and Baldwin Lomax turbulent model for separated flows , can be used efficiently in simulating exactly complex flow fields for large Reynolds number and large attack cases .

在横流理论和wardlaw集中涡法的基础上，通过采用一组合适的自由参数，用半经验半理论的方法计算了无安定器航弹在大攻角情况下的气动特性。

By choosing a group of available free integral parameters , a semiempirical theoretic method based on the crossflow theory and Wardlaw 's concentrated votex method is used to calculate the aerodynamic characteristics of air bomb without fin at hige angle of attack .