翼型

翼型为各种旋转机械的基础，翼型的选用及设计直接影响到旋转机械的整体性能。

Airfoil profile is the basis of various rotating machinery . The selection and designing have a direct effect on the overall performance .

采用型函数扰动法表示翼型廓线，以翼型自身噪声水平作为优化目标，将气动特性作为性能约束，把翼型相对厚度作为形状约束，建立了翼型的优化设计模型。

With the airfoil profile described by using shape function perturbation method , taking the aerodynamic characteristics as the performance constraint and the relative thickness of airfoil as the shape constraint , a noise optimization method is set up with the objective to satisfy the lowest self-noise level .

当进行设计的研究工作后，发现有几种翼型可以用来满足新的性能指标。

As design studies progressed it was found that several airfoil shapes could be used to satisfy the new performance criteria .

改进EGO算法在跨声速翼型气动优化设计中的应用

Application of the Improved EGO Algorithm in Transonic Airfoil Aerodynamic Optimization Design

基于NS方程的跨声速翼型多目标多约束优化设计

Multiobjective Optimization Design of Transonic Airfoils with Constraints Based on Navier-Stokes Equations

应用DES（detachededdysimulation）方法数值模拟了3种不同失速类型的翼型的升力特性。

Detached - Eddy Simulation ( DES ) is applied to three airfoils with different stall types .

Euler方程与边界层积分方程耦合求解跨音速翼型绕流

Transonic airfoil analysis based on the interaction of Euler and integral boundary-layer equation

非结构网格多段翼型绕流Euler及N-S方程数值模拟

Numerical Analysis of Multi-Element Airfoil Using Unstructured Grid and Euler and N-S Equations

基于N-S方程的翼型实验侧壁边界层控制

Side-wall boundary layer removal at airfoil test based on Navier-Stokes equations

Pareto基因算法多目标翼型优化设计

Multi-objective airfoil optimization using Pareto genetic algorithm

基于Kriging模型的翼型多目标气动优化设计研究

Multi-objective Aerodynamic Design Optimization for Airfoil Using Kriging Model

振动翼型跨音速非定常Euler方程数值解方法

Numerical method for solving the Euler equation for unsteady transonic flows over oscillating airfoilss north-western Polytechnical University

基于N-S方程的翼型结冰数值模拟

A Better Numerical Simulation of Ice Accretion on Airfoil

在翼型优化设计中，应用Pareto差分进化算法进行了对翼型的多目标优化设计。

In aerofoil optimization design , Pareto differential evolutional algorithm is used for multi-object optimization design . 4 .

NiAl合金翼型空蚀破坏行为的试验研究

Experimental Study of Cavitation Damage Behaviors of NiAl alloyed Aerofoil

采用非定常N-S方程的翼型颤振特性分析研究

Analysis of Airfoil Flutter Characteristics

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 .

基于2D可压N-S方程，对带扰流板的翼型绕流流场进行非定常数值模拟。

The flowfield around an airfoil with a spoiler is numerically simulated in a time-accurate manner using a 2D compressible Navier-Stokes solver .

本文用FLUENT软件模拟了结冰后NACA0012翼型周围流场的变化，并与结冰前NACA0012翼型的气动性能进行了对比。

The flow field around NACA 0012 airfoil with software Fluent was simulated , to compare the correspondent aerodynamic performance variation before and after icing .

具有Gurney襟翼的多段翼型空气动力特性分析

The analyses of aerodynamic characters of multi-element airfoil with Gurney flap

运用CFD软件，对叶素二维翼型进行了研究，探讨了翼型在不同介质、不同外形结构下的升阻系数和压力情况。

Research on the airfoil using CFD software , investigate the lift / drag ratio and pressure under a variety of media and shape ; 4 .

FBM模型在栅中翼型云状空化流动数值计算中的应用

Application of a Filter-Based Turbulence Model for Cloud Cavitating Flows Around a Cascade Hydrofoil

Gurney襟翼对单段翼型动态气动特性的影响

Effect of Gurney flaps on aerodynamical characters of single airfoil

用不可压缩流动的求解算法，结合WilcoxDC提出的kω模式和kωSST湍流模式，对翼型的动态失速进行了数值模拟。

Dynamic stall of the airfoil is numerically simulated with incompressible flow solver accompanied with the k ω turbulence model proposed by Wilcox D C and the k ω SST turbulence model .

采用CFD手段对两种采用不同叶片翼型的风机进行整机模拟计算，研究了叶片翼型对风机性能的影响。

The effects of two types of airfoil on the performance of multi-blade centrifugal fan used in floor standing air-conditioner are investigated by using the commercial CFD code fluent .

本文分别应用Kriging方法和响应面方法进行了翼型气动优化设计。

In this paper , the Kriging method and the response surface method are both adopted in the aerodynamic optimization design of airfoil .

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 .

本文采用基于余量修正原理的反设计方法，并计入粘性影响，建立了一套基于N-S方程的直升机旋翼翼型的气动设计方法。

Considering viscous effects , an inverse method based on residual correction principle and N-S equations for helicopter rotor aerodynamic airfoils design has been established .

在一定的条件下，Gurney襟翼可以明显增加翼型的升力系数但不过多增加阻力系数。

Under some condition , Gurney flap can increase lift coefficient and lift drag ratio of the airfoil .

基于最优控制理论原理和Navier-Stokes方程，研究了气动/几何约束条件下多设计变量的翼型气动优化设计问题。

Based on the optimal control theory and Navier-Stokes equations , aerodynamic design of airfoil with multi-constraint conditions , such as aerodynamic and geometric constraint conditions , is studied .