迎角

力矩与迎角的关系曲线

Curve of moment against incidence

给定M数和迎角时，可利用计算的多孔翼型的压力分布，来产生外形类似于超临界翼型的实心翼型的压力分布。

For a given Mach number and incidence , the calculated pressure distribution on the airfoil having porous regions , is used to generate the contour of an equivalent solid airfoil whose shape resembles that of an supercritical airfoil .

多段翼型大迎角分离流动的DELAYEDRANS/LES混合算法

DELAYED RANS / LES Method For High Attack Angle Flow over Multi-element Airfoil

跨音速大迎角Euler方程数值分析

A numerical solution of transonic Euler equation at high angles of attack

本文对基于输出反馈RBF神经网络的大迎角非定常气动特性辨识方法进行了研究。

The unsteady aerodynamic identification method based on RBF neural network is studied in this paper .

小迎角轴对称体跨声速绕流的一种Euler解法

An Euler Solution of Transonic Flow for an Axis Symmetric Body at Small Attack

基于RBF神经网络的大迎角机动空空导弹控制系统设计

A / A Missile Control System Design for High Angle of Attack Maneuvering Based on RBF Neural Networks

大迎角体涡、翼涡干扰的Euler方程数值模拟

Numerical Simulation of the Interaction for the Wing-and Body-vortices at High Angle of Attack Using Euler Equations

旋成体大迎角分离流的Euler方程数值模拟

Numerical Simulation of Separation Flow on Bodies of Revolution at High Angle of Attack Using Euler Equations

基于LS-SVM飞机大迎角动态辨识方法研究

A High Angle of Attack Dynamical System Identification Algorithm Based on LS-SVM

利用可压缩层流Navier-Stokes方程模拟了尖头细长体中小迎角的流动结构。

Flow structure around a slender at lower incidences was numerically simulated using time-dependent compressible laminar Navier-Stokes equations .

研究表明：MEMS器件对控制大迎角细长旋成体非对称涡和复杂流场具有良好的控制能力。

The research indicated that MEMS device generate excellent control effect on asymmetric vortices over slender body as well as on complex flow field .

通过数值求解雷诺平均NS方程，研究了二维翼型的大迎角粘性绕流，并分析了翼型的近场旋涡分离流动特性。

Turbulent flows over an airfoil at high angles of attack are investigated numerically by solving the Reynolds averaged Navier Stokes equations .

本文介绍了两种方法来得到迎角和侧滑角的虚拟传感器信号：非线性观测器方法和利用INS／GPS系统数据估计迎角和侧滑角方法。

This paper introduces two methods to get the virtual sensor signal of angle of attack and sideslip angle : Nonlinear Observer method and INS / GPS method .

F-16飞机大迎角飞行偏离/尾旋特性分析

Analysis of Departure / Spin Characteristics of F-16 at High Angle of Attack

当有一个平衡迎角时，可能有一临界Mach数Mcr，当M∞>Mcr时，平衡迎角处是动稳定的；

When there is one trim angle of attack , there probably exists a critical Mach number M_ ( cr ) .

该方法运用了Jameson的旋转差分技术，并采用等效迎角方法计入旋翼尾迹的影响。

Jameson ′ s rotating finite difference methods is adopted and the wake effect is considered by introducing an equivalent angle of attack .

本文运用频率域建模法，分别建立了飞机大迎角滚转运动的Fourier变换模型及非线性代数模型，并从数学模型中提取动导数。

The method of modeling in frequency domain is used to establish the Fourier model and nonlinear algebra model of a rolling aircraft model at high angle of attack . The general dynamic derivatives are extracted from these mathematical models .

在0°~5°的小迎角范围内，求解RNG（RenormalizationGroup）k-ε湍流模型下的N-S方程组，获得与有关单位试验相吻合的数值模拟结果。

By solving RNG ( Renormalization Group ) k-epsilon turbulence N-S Equations over low angle of attack range of 0 ~ 5 °, the numerical simulation result was in good agreement with the relative experiments .

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。

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 .

为验证设计的有效性，在大迎角和两种飞行条件下，将非线性H∞飞行控制系统与线性H∞飞行控制系统的性能进行了对比闭环仿真研究。

To verifying the valid ability , closed simulation comparisons between the performance of the nonlinear H ∞ flight control system and the linear H ∞ flight control system are made on the basis of aircraft dynamic response at high angles of attack and two flight conditions .

介绍了将DMC-PID串级控制技术应用到无人机无动力飞行时的自动着陆阶段迎角自动控制系统。

DMC-PID bunches control technology in the angle of attack automatic control system during unpowered flying automatic landing period is introduced .

为保证TAEM段的窗口约束，以基于动压剖面的规划方法设计迎角过渡段轨迹。

To guarantee the TAEM interface constraints , an analytic trajectory solution based on dynamic pressure programming is presented for the Alpha Transition .

通过与非定常Euler方程的比较，证明该气动力模型具有较高的数值精度，放宽了原始活塞理论对翼型厚度、迎角、马赫数的限制。

The results presented by this model agree well with those of solving unsteady Euler equations . This model greatly reduces the limitations of the classical piston theory on flight Mach number , airfoil thickness , and angle of attack .

采用跨音速小扰动（TSD）方程计算了有迎角的旋转体无分离流动，以及均匀进气假设下机头进气道的外流场。

The transonic flow around the revolution bodies at non-zero angles of attack and the external flow about the nose inlet are calculated by using the transonic small disturbance equation .

将分支分析与突变理论方法（BACTM）和模糊逻辑控制（FLC）方法相结合，形成BACTMFLC方法，实现飞机大迎角下的动力学特性分析和模糊控制律设计一体化。

The bifurcation analysis and catastrophe theory methodology-fuzzy logic control ( BACTM-FLC ) method is developed from bifurcation analysis and catastrophe theory methodology and fuzzy logic control .

本文研究的对象是以小迎角、小侧滑角和一般超音速飞行的旋转弹翼式X-X型导弹。

A missile with tilt-wings in " X-X " configuration is considered in supersonic flight at small angle of attack and sideslip angle .

阐述一种逐点线性化后退区间优化控制（RHO）算法，有效解决小迎角范围内飞机仿射非线性运动控制问题。

This paper proposes the linearization method at each sampling point and Receding Horizon Optimal algorithm ( RHO ), which can solve the control problem of ( nonlinear ) movement of airplane within the range of small attack angle .

结果表明，战斗机F2比F1更具有空中格斗优势，空战中发动机推力、迎角变化率、操纵规律和离轴发射角（μ0）等因素对战斗机过失速机动敏捷性有一定影响。

The results show that PST fighter F2 is superior in the combat , and the facts such as engine thrust , angle of attack rates , control laws and missile off boresight angle have some influence on fighter agility in poststall air combat .

基于多重线涡模型（MLVM），本文建立了一种计算机时少、收敛性强的适用于大迎角涡流势流数值模拟的迭代算法。

A robust iterative method suitable for the numerical simulation of vortex flows at high angles-of-attack is established based upon the multiple line-vortex model ( MLVM ) .