scholarly journals Numerical Study of the Reliability of Wind-Tunnel Wall Corrections for Wingtip Flow

2017 ◽  
Vol 54 (1) ◽  
pp. 354-358 ◽  
Author(s):  
Antoine Joulain ◽  
Damien Desvigne ◽  
David Alfano ◽  
Thomas Leweke
Keyword(s):  
Wind Tunnel ◽  
Numerical Study ◽  
Tunnel Wall

scholarly journals Numerical Study of Wind-Tunnel Wall Effects on Lift and Drag Characteristics of NACA 0012 Airfoil

CFD letters ◽  
2020 ◽  
Vol 12 (11) ◽  
pp. 72-82
Author(s):  
Mostafa Abobaker ◽  
Sogair Addeep ◽  
Abdulhafid M. Elfaghi
Keyword(s):  
Wind Tunnel ◽  
Numerical Study ◽  
Published Data ◽  
Computational Domain ◽  
Tunnel Wall ◽  
Ansys Fluent ◽  
Slope Correction ◽  
Lift Curve ◽  
Lift And Drag ◽  
Naca 0012

Possible interference effects of the wind tunnel walls play an important role especially for measurements in closed-wall test sections. In this study, a numerical analysis of two-dimensional subsonic flow over a NACA 0012 airfoil at different computational domain heights, angles of attack from 0o to 10o, and operating Reynolds number of 6×106 is presented. The work highlights the role of computational fluid dynamics (CFD) in the investigation of wind tunnel wall effect on lift curve slope correction factor (Ka). The flow solution is obtained using Ansys Fluent software by solving the steady-state continuity and momentum governing equations combined with turbulence model k-v shear stress transport (SST-K?). The numerical results are validated by comparing with the available experimental measurements. Calculations show that the lift curve slope correction results are very close to the published data.

Development and Validation of a CFD Technique for the Aerodynamic Analysis of HAWT

2009 ◽  
Vol 131 (3) ◽  
Author(s):  
S. Gómez-Iradi ◽  
R. Steijl ◽  
G. N. Barakos
Keyword(s):  
Wind Tunnel ◽  
Wind Turbine ◽  
Wind Turbines ◽  
Turbine Blades ◽  
Wind Tunnel Test ◽  
Unsteady Aerodynamics ◽  
Tunnel Wall ◽  
Local Flow ◽  
Flow Angle ◽  
Thrust And Torque

This paper demonstrates the potential of a compressible Navier–Stokes CFD method for the analysis of horizontal axis wind turbines. The method was first validated against experimental data of the NREL/NASA-Ames Phase VI (Hand, et al., 2001, “Unsteady Aerodynamics Experiment Phase, VI: Wind Tunnel Test Configurations and Available Data Campaigns,” NREL, Technical Report No. TP-500-29955) wind-tunnel campaign at 7 m/s, 10 m/s, and 20 m/s freestreams for a nonyawed isolated rotor. Comparisons are shown for the surface pressure distributions at several stations along the blades as well as for the integrated thrust and torque values. In addition, a comparison between measurements and CFD results is shown for the local flow angle at several stations ahead of the wind turbine blades. For attached and moderately stalled flow conditions the thrust and torque predictions are fair, though improvements in the stalled flow regime are necessary to avoid overprediction of torque. Subsequently, the wind-tunnel wall effects on the blade aerodynamics, as well as the blade/tower interaction, were investigated. The selected case corresponded to 7 m/s up-wind wind turbine at 0 deg of yaw angle and a rotational speed of 72 rpm. The obtained results suggest that the present method can cope well with the flows encountered around wind turbines providing useful results for their aerodynamic performance and revealing flow details near and off the blades and tower.

Wind-tunnel wall effects on delta wings

1989 ◽  
Vol 26 (5) ◽  
pp. 403-404 ◽  
Author(s):  
Neal T. Frink
Keyword(s):  
Wind Tunnel ◽  
Wall Effects ◽  
Tunnel Wall ◽  
Delta Wings

The multi-functional rotor aerodynamic and aeroacoustic test platform at HKUST

2021 ◽  
Vol 263 (2) ◽  
pp. 4410-4417
Author(s):  
Han Wu ◽  
Chuntai Zheng ◽  
Peng Zhou ◽  
Ryu Fattah ◽  
Xin Zhang ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Phase Locking ◽  
Axial Flow ◽  
Low Noise ◽  
Test Rig ◽  
Tunnel Wall ◽  
Noise Characteristics ◽  
Piv Measurement ◽  
Test Platform ◽  
Semi Empirical

This paper describes the multi-functional rotor noise and aerodynamics test platform at the Hong Kong University of Science and Technology (HKUST). To investigate the noise characteristics of propellers with aerodynamic flows, the test rig is installed in the 2.5×2 (m) low-speed and low-noise wind tunnel in the Aerodynamic and Acoustic Facility (AAF) at HKUST. The wind tunnel can facilitate flow from 0 to 40 m/s. The test rig is assembled in a turntable on the ceiling of the tunnel wall, which enables the testing range of pitch angle can vary from 0° (axial flow) to 90° (parallel flow), with an accuracy of 0.1°. The noise produced by the rotor is measured by a set of wall-mounted surface microphones. Semi-empirical calibration is conducted to quantify the noise reflection by the tunnel walls. A low-noise struct has been designed and manufactured to locate a set of far-field microphones equipped with nosecone, to improve the quality of acoustic measurement inside the flow. In addition, a synchronized system is developed to conduct the phase-locking Particle Image Velocimetry (PIV) measurement on the rotor, to study the flow pattern to better understand the noise generation mechanism.

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