scholarly journals Design and Development of a Gas Dynamics Facility and a Supersonic Wind Tunnel

10.5772/52988 ◽  
2013 ◽  
Author(s):  
N. A.
Keyword(s):  
Wind Tunnel ◽  
Gas Dynamics ◽  
Design And Development ◽  
Supersonic Wind Tunnel

Study on Correlation between Geometrical Correction and Aerodynamic Performance of Microscale Supersonic Wind Tunnel

2018 ◽  
Vol 138 (4) ◽  
pp. 145-152
Author(s):  
Naoki Murai ◽  
Ryouto Yamamoto ◽  
Kouhei Rikuno ◽  
Toshiyuki Toriyama
Keyword(s):  
Wind Tunnel ◽  
Aerodynamic Performance ◽  
Supersonic Wind Tunnel

scholarly journals Condensation effects on Rayleigh scattering measurements in a supersonic wind tunnel

AIAA Journal ◽  
1991 ◽  
Vol 29 (2) ◽  
pp. 242-246 ◽  
Author(s):  
B. Shirinzadeh ◽  
M. E. Hillard ◽  
R. J. Exton
Keyword(s):  
Wind Tunnel ◽  
Rayleigh Scattering ◽  
Supersonic Wind Tunnel ◽  
Scattering Measurements

scholarly journals Model Deformation Measurements of Sonic Boom Models in the NASA Ames 9- by 7- Ft Supersonic Wind Tunnel

2015 ◽  
Author(s):  
Edward T. Schairer ◽  
Laura K. Kushner ◽  
Theodore J. Garbeff ◽  
James T. Heineck
Keyword(s):  
Wind Tunnel ◽  
Sonic Boom ◽  
Supersonic Wind Tunnel ◽  
Deformation Measurements

Flow characteristics of the NASA-Ames laminar supersonic wind tunnel for Mach 1.6 operation

1994 ◽  
Author(s):  
Stephen Wolf ◽  
James Laub ◽  
Lyndell King
Keyword(s):  
Wind Tunnel ◽  
Flow Characteristics ◽  
Supersonic Wind Tunnel

ADVANCED DESIGN FEATURES IN CANADA'S SUPERSONIC WIND TUNNEL

1962 ◽  
Author(s):  
L. C. Secord ◽  
L. J. P. Tillson
Keyword(s):  
Wind Tunnel ◽  
Design Features ◽  
Supersonic Wind Tunnel

scholarly journals Supersonic Windtunnel Noise Attenuation

2021 ◽  
Author(s):  
William Wai Lim Wong
Keyword(s):  
Wind Tunnel ◽  
Sound Pressure Level ◽  
Noise Level ◽  
Sound Pressure ◽  
Power Level ◽  
Mesh Size ◽  
Acoustic Power ◽  
Pressure Level ◽  
Supersonic Wind Tunnel ◽  
Acoustic Treatment

The aerodynamic generated noise in the supersonic wind tunnel during operation at Ryerson University has exceeded the threshold of hearing damage. An acoustic silencer was to be designed and added to the wind tunnel to reduce the noise level. The main sources of noise generated from the wind tunnel with the silencer were identified to be located at the convergent divergent nozzle and the turbulent region downstream of the shock wave at the diffuser with the maximum acoustic power level of the entire wind tunnel at 161.09 dB. The designed silencer provided an overall sound pressure level reduction of 21.41 db which was considered as acceptable. Refinement to the mesh size and changes to the geometry of the mixing chamber was suggested for a more accurate result in noise output as well as flow conditions would match up to the physical flow. Additional acoustic treatment should be applied to the wind tunnel to further reduce sound pressure level since the noise level still exceeded the threshold of hearing loss.

scholarly journals Experimental Measurements of Starting Loads and Model Behaviors in the Indraft Supersonic Wind Tunnel

2010 ◽  
Vol 53 (179) ◽  
pp. 54-62 ◽  
Author(s):  
Ryojiro MINATO ◽  
Kazuhide MIZOBATA ◽  
Komei KUWATA
Keyword(s):  
Wind Tunnel ◽  
Experimental Measurements ◽  
Supersonic Wind Tunnel

New Supersonic Wind Tunnel

1956 ◽  
Vol 261 (4) ◽  
pp. 470
Keyword(s):  
Wind Tunnel ◽  
Supersonic Wind Tunnel
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