Wind tunnel noise measurements on full‐scale pantograph models

1999 ◽  
Vol 105 (2) ◽  
pp. 1136-1136 ◽  
Author(s):  
Thomas Lölgen
Keyword(s):  
Wind Tunnel ◽  
Full Scale ◽  
Noise Measurements

scholarly journals Comparing flyover noise measurements to full-scale nose landing gear wind tunnel experiments for regional aircraft

2017 ◽  
Author(s):  
Roberto Merino Martinez ◽  
Eleonora Neri ◽  
Mirjam Snellen ◽  
John Kennedy ◽  
Dick Simons ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Landing Gear ◽  
Full Scale ◽  
Wind Tunnel Experiments ◽  
Noise Measurements

Wind Tunnel to Full Scale Mapping of Winds and Loads for Launch-Vehicle Ground Wind Loads

2021 ◽  
Author(s):  
Thomas G. Ivanco ◽  
Donald F. Keller ◽  
Jennifer L. Pinkerton
Keyword(s):  
Wind Tunnel ◽  
Launch Vehicle ◽  
Full Scale ◽  
Wind Loads

Characterization of wind-induced pressure on membrane roofs based on full-scale wind tunnel testing

2021 ◽  
Vol 235 ◽  
pp. 112101
Author(s):  
Johnny Estephan ◽  
Changda Feng ◽  
Arindam Gan Chowdhury ◽  
Mauricio Chavez ◽  
Appupillai Baskaran ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Full Scale ◽  
Wind Tunnel Testing ◽  
Tunnel Testing

Wind Tunnel Noise Measurements

1960 ◽  
Vol 32 (7) ◽  
pp. 932-932
Author(s):  
William J. Galloway
Keyword(s):  
Wind Tunnel ◽  
Noise Measurements

A New Method of Modeling Underexpanded Exhaust Plumes for Wind Tunnel Aerodynamic Testing

1989 ◽  
Vol 111 (4) ◽  
pp. 748-754
Author(s):  
V. Salemann ◽  
J. M. Williams
Keyword(s):  
Wind Tunnel ◽  
Free Stream ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Area Ratio ◽  
Full Scale ◽  
New Method ◽  
Thrust Coefficient ◽  
Model Scale ◽  
Exhaust Plumes

A new method for modeling hot underexpanded exhaust plumes with cold model scale plumes in aerodynamic wind tunnel testing has been developed. The method is applicable to aeropropulsion testing where significant interaction between the exhaust and the free stream and aftbody may be present. The technique scales the model and nozzle external geometry, including the nozzle exit area, matches the model jet to free-stream dynamic pressure ratio to full-scale jet to free-stream dynamic pressure ratio, and matches the model thrust coefficient to full-scale thrust coefficient. The technique does not require scaling of the internal nozzle geometry. A generalized method of characteristic computer code was used to predict the plume shapes of a hot (γ = 1.2) half-scale nozzle of area ratio 3.2 and of a cold (γ = 1.4) model scale nozzle of area ratio 1.3, whose pressure ratio and area ratio were selected to satisfy the above criteria and other testing requirements. The plume shapes showed good agreement. Code validity was checked by comparing code results for cold air exhausting into a quiescent atmosphere to pilot surveys and shadowgraphs of model nozzle plumes taken in a static facility.

Airframe noise measurements in a large hard-walled closed-section wind tunnel

2019 ◽  
Vol 146 ◽  
pp. 96-107 ◽  
Author(s):  
Alessandro Di Marco ◽  
Lorenzo Burghignoli ◽  
Francesco Centracchio ◽  
Roberto Camussi ◽  
Thomas Ahlefeldt ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Airframe Noise ◽  
Noise Measurements
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