主要介绍了一种低速风洞模型姿态控制系统的组成。
This paper introduces composition of the kind of control system of model gesture in low speed wind-tunnel.
设计了模型和实验装置，进行了大迎角低速风洞实验。
The experimental model and equipment are designed, and the low speed wind tunnel experiment at high angles of attack is made.
介绍了一种简洁有效的低速风洞收缩段的设计、加工以及校验的方法。
A method that can be used to design, manufacture and test the contraction section of a wind tunnel is presented.
介绍一种用于森林保护科研试验的低速风洞的构造、性能和设计原理。
A type of low speed wind tunnel used in research on forestry protection and its structure, function and principle of the design is introduced.
本文对动失速型非定常分离流的主动控制方法在低速风洞中进行了实验研究。
An experimental investigation on the active control of dynamic stall type unsteady separated flow is carried out in the low speed wind tunnel using a phase averaged pressure measurement technique.
利用热线风速仪，对光滑表面和多个脊状表面在低速风洞中进行了表面流场测试。
Exterior flow field measurement above smooth and different riblet surfaces was carried out in a low speed wind tunnel by means of hot-wire anemometry.
采用富士plc、人机界面与变频器实现了低速风洞数据采集和风速的闭环控制。
The low speed wind tunnel data acquiring and the closed loop controlling of wind velocity are realized by PLC and human machine interface and inverter from Fuji.
与在南航NH-2低速风洞中的实验结果比较表明，计算方法和优化设计是成功的。
The tests in NH-2 low speed wind tunnel at Nanjing University of Aeronautics and Astronautics showed good agreement between computation and test values.
通过实验研究证明了用主流阻尼器快速调节半开口直流式低速风洞的实验风速的可行性。
For a low speed blow down wind tunnel with semi-open test section, the effectiveness of main flow damper in rapidly changing test velocity is verified through experimental research.
本文简要地阐述了具有后缘控制面的二元机翼模型主动颤振抑制低速风洞试验的全过程。
This paper gives a brief description of the whole process of the low-speed wind tunnel test for active flutter suppression of a two-dimensional wing model with trailing edge control surface.
大型低速风洞测控自动化的难点是大型动力系统的自动化和大型变角控制系统的自动化。
The difficult problem of the automatization of measurement and CDntrol in the large low speed wind tunnel is an automatization of large power system and large Angle control system.
采用实验方法对某型弹用涡扇发动机涡轮低压导向器原型和改型进行了详细的低速风洞实验。
Detailed flow field measurements were conducted in a low speed wind tunnel for both original and modified LGV's which are used in turbofan engines.
介绍原山东工业大学小型低速风洞的技术参数、数据采集与处理系统的硬件结构和软件设计。
The technical parameter, hardware structure and software design of the data acquiring and processing system of the small Low Speed Wind Tunnel in Shandong University of Technology are introduced.
基于对飞机模型在不同姿态下进行的空气动力学测试，文中设计了用于低速风洞的变角度系统。
Based on the aerodynamic test of plane models under different positions, the variable Angle system used in low-speed wind tunnels is designed in this paper.
沥青瓦抗风性试验仪由风源、试验平台和控制系统三大部分组成，它是一种民用开式低速风洞。
The tester, a kind of civil low speed wind tunnel in nature, consists of wind generator, test platform and control system.
基于传统的风洞试验支撑设备，设计了用于低速风洞测量大攻角模型支架干扰的组合支撑设备。
Based on traditional support system in wind tunnel testing, the combination support system measuring support interference on high angles of attack model in low speed wind tunnel was designed.
开口低速风洞的主要组成部分包括集气装置、蜂窝器、紊流网、整流罩和叶栅型反扭导流片等。
Low-speed wind tunnel opening of the main components of gas-collecting devices, cellular devices, tangled net, fairing and cascade-type deflector, such as anti-twisting.
基于传统的风洞试验支撑设备，设计了用于低速风洞测量大攻角模型支架干扰的组合支撑设备。
A "Separating model and support (SMS) method" for measuring support interference is proposed according to the analysis of the support interference for vehicle model wind tunnel tests in this paper.
开口低速风洞的主要组成部分包括集气装置、蜂窝器、紊流网、整流罩和叶栅型反扭导流片等。
Its main components include gas collecting devices, cellular devices, turbulent mesh, fairing, cascade-type counterclockwise shearing deflector, and etc.
由涡的定义导出的向量泊桑方程的积分形式的解析解，被用于低速风洞壁引起的干扰速度的计算。
The analytical solution of Poisson's equation, derived from the definition of vortex, has been applied to the calculations of interference velocities due to the presence of wind tunnel walls.
低速风洞实验要求对实验段的风速有严格的控制，要求风速调节范围宽，精度指标高，调节速度快。
Low speed wind tunnel experiment requires strict of the wind speed, which requires a wild range of wind speed, high precision, and quick adjustment.
本文对动失速型非定常分离涡结构的控制方法，在低速风洞中应用相平均测压技术进行了实验研究。
Experimental investigation on the control of dynamic stall type vortex flow was made in a low speed wind tunnel by using phase averaged pressure measurement technique.
用低速风洞测力试验和襟翼处绕流的PIV测量试验研究锯齿形格尼襟翼在不同偏角下的增升效益。
Force and PIV local flow measurements were conducted in a low speed wind tunnel to study the effectiveness of serrated Gurney flap at different deflections.
为了研究飞行器在纵向大迎角状态下的动态失速现象，设计了一套用于低速风洞的升沉振动测量装置。
In order to study dynamic stall phenomena of an aircraft in portrait at a high Angle of attack, designing a measuring device of heave oscillation for a low speed wind tunnel.
在低速风洞上，对某型弹用涡扇发动机涡轮低压导向器原型和改型进行了变工况条件下的详细流场测量。
Experimental measurements were performed in a low speed wind tunnel for both original and modified turbine LGV's which are used in turbofan engines under different operating conditions.
利用二维粒子图像测速系统研究了低速风洞实验中介质阻挡放电等离子体对圆柱绕流尾迹区流场的影响。
Two dimensional particle image velocimetry system is used to investigate effects of the dielectric barrier discharge plasma on the flow field in the wake of circular cylinder cross flow.
鉴于风洞试验已扩展到更高的速度范围，因此有必要将原著《风洞试验》一书进行修订，并分编为《高速风洞试验》和《低速风洞试验》两部出版。
The extension of the field of wind tunnel testing into the higher-speed regimes has made it advisable to revise Wind Tunnel Testing into low-and high -speed coverages .
在大尺寸低速开式叶栅传热风洞中对一种高压涡轮导向叶栅中的流场进行了流动显示实验研究。
The flow field visualization of a straight HP turbine cascade is conducted in a large-scale low-speed open -loop cascade heat transfer wind tunnel.
根据航空发动机设计的实际需要，在大尺寸低速叶栅传热风洞中对涡轮叶片表面的气膜冷却进行了综合性实验研究。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine.
根据航空发动机设计的实际需要，在大尺寸低速叶栅传热风洞中对涡轮叶片表面的气膜冷却进行了综合性实验研究。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine.
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