Qualification of the ARA TWT for laminar flow testing

2014 ◽  
Vol 118 (1209) ◽  
pp. 1349-1358 ◽  
Author(s):  
N. Allen ◽  
S. Lawson ◽  
M. Maina ◽  
J. Alderman
Keyword(s):  
Wind Tunnel ◽  
Laminar Flow ◽  
Large Scale ◽  
Wind Tunnel Test ◽  
Performance Testing ◽  
Current Drive ◽  
Future Research ◽  
Temperature Sensitive ◽  
Tollmien Schlichting ◽  
Natural Laminar Flow

Abstract The current drive towards reducing the environmental impact of aircraft necessitates the ability to evaluate techniques for promoting natural laminar flow in a large scale wind tunnel facility. A test was undertaken on the M2355 variable sweep model to obtain temperature sensitive paint (TSP) and hot-film data from which the transition locations at a range of sweep angles and flow conditions could be identified. The TSP technique has been shown to be a reliable method for determining transition on suitably treated wind tunnel models. Pressure data were also acquired and interpolated to provide the input to the laminar boundary layer code, BL2D, the output from which was used in the linear stability analysis code, CoDS, to calculate the N-factor for the ARA TWT (Transonic Wind Tunnel) facility. Two sets of N-factors were calculated, firstly using incompressible analysis with stationary crossflow and secondly using compressible analysis with travelling crossflow. In both analyses the Tollmien-Schlichting and crossflow cases were calculated together, rather than separating the cases before running the analysis. The resulting N-factors indicate a degree of scatter typical for experimental data. The N-factor based on incompressible theory for crossflow was found to be approximately 7 and for Tollmien-Schlichting (T-S), approximately 11. The results of the wind tunnel test and the analysis carried out are considered to be the first steps towards establishing a methodology for performance testing, in atmospheric tunnels such as the TWT, for aircraft designed to have significant regions of laminar flow. The project has also provided a body of experimental test data which will be valuable for future research into development and validation of laminar flow methods.

The Stability Analysis of the Driving Rod of the Wind Tunnel Test Model Based on Workbench

2015 ◽  
Vol 799-800 ◽  
pp. 538-542
Author(s):  
Zi Yan Shao ◽  
Wen Jia Chen ◽  
Yong Jin Hu ◽  
Guan Jian Li
Keyword(s):  
Wind Tunnel ◽  
Degrees Of Freedom ◽  
Wind Tunnel Test ◽  
Future Research ◽  
Response Analysis ◽  
Test Model ◽  
Main Research ◽  
Theoretical Support ◽  
Harmonic Response Analysis ◽  
The Stability

The ANSYS Workbench is used in this paper to analyse a kind of wind tunnel test model support platform with 5 degrees of freedom. The driving rod of the pitch motion is chosen as the main research project. By using static structural analysis, modal analysis and harmonic response analysis, a detailed analysis is made on the stress, deformation and frequency of the driving rod, and provides theoretical support for the future research on the stability of the institution.

scholarly journals Scaling Method of the Rotating Blade of a Wind Turbine for a Rime Ice Wind Tunnel Test

Energies ◽  
2019 ◽  
Vol 12 (4) ◽  
pp. 627 ◽  
Author(s):  
Yan Li ◽  
Ce Sun ◽  
Yu Jiang ◽  
Fang Feng
Keyword(s):  
Heat Transfer ◽  
Wind Tunnel ◽  
Large Scale ◽  
Wind Tunnel Test ◽  
Full Scale ◽  
Similar Degree ◽  
Transfer Model ◽  
Ice Accretion ◽  
Water Droplets ◽  
Scaling Method

In order to research the law of rime ice accretion on different scaling blades surface, a new rime ice scaling method was proposed in this research. According to previous research, there are three kinds of ice types on blade surfaces: rime ice, glaze ice and mixed ice. Under the condition of rime ice, both the freezing fraction and the coefficient of heat transfer between super-cold water droplets and blade are 100%. The heat transfer model of rime ice is simpler than that of glaze ice and mixed ice. In this research, the scaling parameters including flow field, water droplets, temperature, pressure and rotating parameters were defined. The Weber number (We) based on water film thickness as an important parameter was applied in this study. The rotating parameters including rotating speed and radius had been added into the icing scaling method. To verify the effectiveness of the new rime ice scaling method, icing wind tunnel tests were carried out. The NACA0018 airfoil was used for the test blade. Two kinds of scale chord blades were selected, the chord of full-scale blade was 200 mm and of subscale blade was 100 mm. The test temperature was −15 °C. The ice accretion on different scale blades surface were captured by high-speed camera and the icing shapes of different scaling blades were obtained. To quantitatively analyze the similar degree of icing shapes on different scale blades, an evaluation method which included similar degree (Sim) was established based on the typical characteristic parameters proposed by previous research. The results show that the icing shapes of subscale blades are similar to that of full-scale blades. The similar degree is between 75.22% and 93.01%. The icing wind tunnel test indicates that the new rime ice scaling method is an effective method to study the rime ice of large scale rotating blades. This study can be used as a reference for research on anti-icing and de-icing technologies for large-scale HAWTs (Horizontal Axis Wind Turbines).

Feasibility investigation of large-scale model suspended by cable-driven parallel robot in hypersonic wind tunnel test

2016 ◽  
Vol 231 (13) ◽  
pp. 2375-2383 ◽  
Author(s):  
Xiaoguang Wang ◽  
Miaojiao Peng ◽  
Zhenghong Hu ◽  
Yueshi Chen ◽  
Qi Lin
Keyword(s):  
Wind Tunnel ◽  
Large Scale ◽  
Cfd Simulation ◽  
Aerodynamic Force ◽  
Wind Tunnel Test ◽  
Special Kind ◽  
Parallel Robot ◽  
Scale Model ◽  
Hypersonic Wind Tunnel ◽  
Large Scale Model

Cable-driven parallel robot is a special kind of robot, which is actuated by cables. It is already applied in the low speed wind tunnel to get aerodynamic measurement of aircraft model, and the aircraft pose could be adjusted by changing the cable length. Whether it can be used in hypersonic wind tunnel still needs further discussion. This paper presents the dynamics and aerodynamics analysis of a large-scale model supported by 6-DOF cable-driven parallel robot to investigate the feasibility of this special kind of suspension system in hypersonic wind tunnel. The description of this setup with a X-51A-like model is given, and then based on the system dynamic equations, aerodynamic force and stiffness matrix are derived. In the simulation, properties of dynamics and aerodynamics are mainly concerned. A typical shock tunnel with flow duration of about 100 milliseconds is taken as an example, and results show that the system is stable enough to meet the fundamental static wind tunnel test. From the cable tension variation under impact load and the sensitivity analysis, it is likely accessible to derive the aerodynamic forces. Compared with the sting suspension method, cable-driven parallel robot has the priority of higher inherent frequency and more flexible degrees. The interference to the flow field induced by cables is also preliminarily proved to be small by the CFD simulation, which can be acceptable and corrected. Researches conducted show the feasibility of cable-driven parallel robot’s application in hypersonic wind tunnel.

Fluidic actuators for separation control at the engine/wing junction

2017 ◽  
Vol 89 (5) ◽  
pp. 709-718 ◽  
Author(s):  
Philipp Schloesser ◽  
Michael Meyer ◽  
Martin Schueller ◽  
Perez Weigel ◽  
Matthias Bauer
Keyword(s):  
Wind Tunnel ◽  
Flow Control ◽  
Flow Separation ◽  
Mass Flux ◽  
Large Scale ◽  
Active Flow Control ◽  
Wind Tunnel Test ◽  
Local Flow ◽  
Content Type ◽  
Active Flow

Purpose The area behind the engine/wing junction of conventional civil aircraft configurations with underwing-mounted turbofans is susceptible to local flow separation at high angles of attack, which potentially impacts maximum lift performance of the aircraft. This paper aims to present the design, testing and optimization of two distinct systems of fluidic actuation dedicated to reduce separation at the engine/wing junction. Design/methodology/approach Active flow control applied at the unprotected leading edge inboard of the engine pylon has shown considerable potential to alleviate or even eliminate local flow separation, and consequently regain maximum lift performance. Two actuator systems, pulsed jet actuators with and without net mass flux, are tested and optimized with respect to an upcoming large-scale wind tunnel test to assess the effect of active flow control on the flow behavior. The requirements and parameters of the flow control hardware are set by numerical simulations of project partners. Findings The results of ground test show that full modulation of the jets of the non-zero mass flux actuator is achieved. In addition, it could be shown that the required parameters can be satisfied at design mass flow, and that pressure levels are within bounds. Furthermore, a new generation of zero-net mass flux actuators with improved performance is presented and described. This flow control system includes the actuator devices, their integration, as well as the drive and control electronics system that is used to drive groups of actuators. Originality/value The originality is given by the application of the two flow control systems in a scheduled large-scale wind tunnel test.

Large Scale Pressurized Water Reactor Passive Containment Cooling System Wind Tunnel Test

2019 ◽  
Vol 5 (3) ◽  
Author(s):  
Huang Jingyu ◽  
Pan Xinxin ◽  
Song Chunjing
Keyword(s):  
Wind Tunnel ◽  
Large Scale ◽  
Cooling System ◽  
Air Flow ◽  
Wind Tunnel Test ◽  
Pressurized Water Reactor ◽  
Scaled Model ◽  
Pressurized Water ◽  
Water Reactor ◽  
Wind Speeds

The objective of the current work is to shed light on studying the air flow features of the air path which is part of the passive containment cooling system (PCS) in a pressurized water reactor design. A wind tunnel test using a 1:100 scaled model is established to study the characteristic called “wind-neutrality” of the air flow in the air path, which indicates that the environmental wind should not be beneficial or detrimental to the air flow for containment cooling. Test results show that the pressure distribution in the air path is uniform, and wind speeds, wind angles, and surroundings have little effect on air flow uniformity. These investigations show that it is possible to understand air flows in the air path of PCS with a scale wind tunnel test.

Review of MEMS Techniques and Applications in Aerodynamics Research

2014 ◽  
Vol 596 ◽  
pp. 532-535
Author(s):  
Li Tao Fan
Keyword(s):  
Wind Tunnel ◽  
Low Cost ◽  
Wind Tunnel Test ◽  
Future Research ◽  
Mems Sensors ◽  
Research Focus ◽  
Basic Principles ◽  
Wind Tunnel Tests ◽  
Mems Technology

MEMS sensors have some attractive advantages, such as low cost, small size, which help them to be widely used in wind tunnel tests. This paper presents the basic principles and sensor types of MEMS measurement and concludes the MEMS technology for wind tunnel test applications. Future research focus is also expressed.

Sign in / Sign up

Export Citation Format

Share Document