An experimental investigation of the static pressure fluctuation mechanism for porous transonic wind tunnel wall configurations

1993 ◽  
Vol 15 (6) ◽  
pp. 401-410
Author(s):  
B. L. Medved
Keyword(s):  
Experimental Investigation ◽  
Wind Tunnel ◽  
Pressure Fluctuation ◽  
Static Pressure ◽  
Tunnel Wall ◽  
Transonic Wind Tunnel

The Experimental Investigation of Jet Fan Aerodynamics Using Wind Tunnel Modeling

1996 ◽  
Vol 118 (2) ◽  
pp. 322-328 ◽  
Author(s):  
K. R. Mutama ◽  
A. E. Hall
Keyword(s):  
Experimental Investigation ◽  
Pressure Drop ◽  
Wind Tunnel ◽  
Initial Pressure ◽  
Tunnel Wall ◽  
Tunnel Ventilation ◽  
Significant Length ◽  
Complete Set ◽  
Jet Fan ◽  
Jet Oscillation

Jet fan aerodynamic behavior was investigated using wind tunnel modeling. Conditions were created to simulate mine and vehicular tunnel ventilation where these fans are finding increased application. Results showed that the ability of a jet fan to entrain air depends on its proximity to the tunnel wall. Moving the jet fan toward the wall increased the initial pressure drop below ambient in a significant length of the tunnel. This increased the volume of air entrained despite the existence of a large recirculation eddy or back flow whose size diminished as the jet fan was traversed toward the tunnel axis. When the jet fan was located at the tunnel axis the flow was very unstable close to the walls of the tunnel and it had a tendency to reverse itself with periods coinciding with the jet oscillation behavior. The complete set of measurements obtained are suitable for CFD code validation and modeling.

Transonic wind-tunnel wall interference prediction code

1990 ◽  
Vol 27 (11) ◽  
pp. 915-916 ◽  
Author(s):  
Pamela S. Phillips ◽  
Edgar G. Waggoner
Keyword(s):  
Wind Tunnel ◽  
Tunnel Wall ◽  
Transonic Wind Tunnel

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.

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