Wind Tunnel Wall Interference.

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.

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Wind-tunnel wall effects on delta wings

Journal of Aircraft ◽

10.2514/3.45776 ◽

1989 ◽

Vol 26 (5) ◽

pp. 403-404 ◽

Cited By ~ 1

Author(s):

Neal T. Frink

Keyword(s):

Wind Tunnel ◽

Wall Effects ◽

Tunnel Wall ◽

Delta Wings

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A CFD Investigation of Wind Tunnel Wall Influences on Pitching Delta Wings

20th AIAA Applied Aerodynamics Conference ◽

10.2514/6.2002-2938 ◽

2002 ◽

Cited By ~ 3

Author(s):

Mark Allan ◽

Ken Badcock ◽

Bryan Richards

Keyword(s):

Wind Tunnel ◽

Tunnel Wall ◽

Delta Wings

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

INTER-NOISE and NOISE-CON Congress and Conference Proceedings ◽

10.3397/in-2021-2695 ◽

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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