Wind Tunnel Wall Corrections Deduced by Iterating from Measured Wall Static Pressure

AIAA Journal ◽  
1983 ◽  
Vol 21 (12) ◽  
pp. 1667-1673 ◽  
Author(s):  
D. F. Moses
Keyword(s):  
Wind Tunnel ◽  
Static Pressure ◽  
Tunnel Wall

scholarly journals Airfoil lift calculation using wind tunnel wall pressures

2021 ◽  
pp. 095441002110382
Author(s):  
Sreevishnu Oruganti ◽  
Shreyas Narsipur
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Static Pressure ◽  
Reference Data ◽  
Measurement Techniques ◽  
Surface Flow ◽  
Flow Conditions ◽  
Tunnel Wall ◽  
Number Range ◽  
Sensitivity Studies

An experimental method to calculate lift using static pressure ports on the wind tunnel walls and its associated limits has been explored in this article. While the wall-pressure measurement (WPM) technique for lift calculation has been implemented by other researchers, there is a lack of literature on the sensitivity of the WPM method to airfoil chord length, model thickness, surface roughness, and freestream conditions. Chord sensitivity studies showed that the airfoil chord to test section length ratio plays an important role in the accuracy of the measurements. Models need to be appropriately sized for optimum performance of the WPM method. Additionally, choosing the correct scaling ratio also ensures independence of lift measurements from freestream Reynolds number conditions. Finally, a combination of symmetric and cambered airfoils with thicknesses varying from 6 % − 21 % were tested and successfully validated against reference data for a freestream chord Reynolds number range of 100,000 to 550,000. The WPM method was found to be sensitive to varying surface flow conditions and airfoil thickness and has been shown to be a viable replacement to traditional lift measurement techniques using load balances or airfoils with surface pressure ports.

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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