涵道

基于动量源方法的涵道尾桨CFD分析

CFD Analysis for the Ducted Tail Rotor Based on Momentum-Source Method

前飞状态涵道尾桨气动特性CFD分析

CFD Analysis for the Ducted Tail Rotor in Forward Flight

涵道尾桨的CFD模拟与验证带附体潜艇尾流场的数值模拟与验证

CFD Simulation and Validation of Ducted Tail Rotor Numerical Simulation and Validation of Wake Field of Submarine with Stern Appendage

本文采用CFD方法分析了悬停状态下涵道尾桨的流场特性。

The flow field characteristic of a helicopter ducted tail rotor in hovering were analyzed using CFD method in this paper .

采用CFD（计算流体力学）方法分析在悬停和侧飞时直升机涵道尾桨的流场与性能。

The flow field and performance of a helicopter ducted tail rotor in hovering and sideward flight were analyzed using CFD ( Computational Fluid Dynamic ) technique .

本文建立了一套通过求解湍流Navier-Stokes方程并结合动量源模型，来分析涵道尾桨流场和气动特性的方法。

In this thesis , a numerical simulation method is established by solving the turbulent Navier-Stokes equations coupled with the momentum source model .

使用三维数值模拟软件NUMECA（NumericalMechanicsApplication）对双涵道风扇/增压级带转子叶尖间隙的粘性流场进行了三维定常流动数值模拟，获得了其设计转速下的流场特性。

A three dimension numerical simulation software named NUMECA ( numerical mechanics application ) was used to calculate the tip clearance flow of fan / compressor . The flow field performance under design speed condition was obtained .

为了研究涵道风扇系统的气动特性，尤其是在复杂流场中涵道本身的升阻特性，在3.4m×2.4m开口风洞中对涵道风扇进行了吹风试验。

An experimental research is completed in a 3 4 m × 2 4 m wind tunnel , the purpose is to determine the aerodynamic characteristics of a ducted fan system , especially the lift and drag of the duct in the complex airflow .

小型涵道式无人机控制系统设计实现

Design and Realization of Control System for Small Ducted Fan UAV

旋翼/涵道风扇共轴式无人直升机操稳特性研究

Stability and control analysis of rotor / ducted-fan based unmanned helicopter

涵道风扇升力系统的升阻特性试验研究

Experimental Investigation on Lift and Drag of Ducted Fan System

直升机悬停时涵道尾桨的需用功率计算

A Method for Predicting Ducted Tail Rotor Power Required in Hovering Flight

涵道风扇式无人机结构布局及其叶片空气动力学分析

Structure Layout and Vane Aerodynamics Analysis on Ducted Fan UAV

高速直升机涵道风扇矢量推进系统模型悬停状态的气动力测量研究

Measurement investigation on the aerodynamics of vectored thrust ducted propeller

直升机涵道尾桨与孤立尾桨的气动特性对比研究

Comparison and Analysis of Aerodynamic characteristics between Helicopter Shrouded and Isolated Tail Rotors

CFM56-3/-7发动机涵道清洗经验探讨

The Experience Discuss of Water Wash on CFM 56-3 / - 7 Engine

吊舱发电系统涵道式冲压空气涡轮叶片性能的研究

Research on Ducted Ram Air Turbine Blade Properties for Pod Power Supply System

多声路超声波流量计在变断面涵道流量测量中的应用

Application of multi-path ultrasonic flow measurement to variable-section conduits

一种涵道螺旋桨优化设计新方法研究

A Special Method of Optimum Design for Ducted Propeller

地效翼船用涵道螺旋桨的设计试验

The Duct Fan Design and Test for WIG Craft

双涵道叶轮机S2流面反问题计算方法

A revised program for the bypass turbomachine inverse problem of flow along s_2 surface

涵道风扇空气动力学特性分析

Aerodynamical Characteristics Analysis of Ducted Fan

低速大迎角下机腹双弯涵道空气动力性质研究

Research of Aerodynamic Characteristics for Double-bend Inlet in the Situation of High Incidence and Low Speed

本文介绍了某型飞机发动机外涵道整流罩的国产化研制技术；

The domestic manufacturing technology for the external duct fairing of aeroengine is introduced in this paper .

该新型无人直升机采用单旋翼涵道风扇式构形、双发动机的布局。

The new unmanned helicopter is constructed by single rotor and ducted fan , who has two engines .

某新型无人直升机采用单旋翼涵道风扇双发动机对称式布局，克服了单发动机输出功率不足的问题。

For the single rotor autonomous helicopter with ducted fan , the sufficient power is supplied by twin-engine .

在车体封闭摩托车风罩上开风口、涵道增强冷却效果；

The vent and culvert on the wind shield of closeded body motorcycle can better the cooling effect ;

涵道风扇无人机的姿态调整是其控制的一个关键点也是一个难点。

The position adjustment is both a key technology and difficult point for control of the ducted fan UAV .

在非结构网格上对二维高超声速化学非平衡粘性绕流进行了数值模拟，并应用此方法对涵道构型高超声速减阻特性进行了数值分析。

Numerical methods for hypersonic flow with chemical non-equilibrium reactions on the unstructured grid are used to analyze the drag induction of channel-configurations .

由于地效翼船不同于普遍意义上的飞行器，它的巡航速度低，航空涵道螺旋桨相对的设计速度较高，而国内缺乏对涵道螺旋桨的系统研究。

WIG Craft differs from aircraft , it possesses the low cruising speed . So far there is less research work on it domestically .