Reduction of acoustic disturbances in the test section of supersonic wind tunnels by laminarizing their nozzle and test section wall boundary layers by means of suction [PDF]
The feasibility of quiet, suction laminarized, high Reynolds number (Re) supersonic wind tunnel nozzles was studied. According to nozzle wall boundary layer development and stability studies, relatively weak area suction can prevent amplified nozzle wall
Pfenninger, W., Syberg, J.
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Effective of Passive Devices in Alleviation of Flow-induced oscillations of he nozzles of a Multi-Booster Launch vehicle [PDF]
, 2011 Wind tunnel tests to quantify the flow induced oscillations of nozzles of strap-on boosters of a typical launch vehicle have been performed under jet-off conditions in the Mach number range 0.8 to 2.5. The effects of gymballing the nozzles on the steady
Nagarajan, V, Suryanarayana, GK
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Pressure-Sensitive Paint Measurements on a Moving Store in the NRC 1.5 m Blowdown Wind Tunnel
32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 2016 The pressure-sensitive paint technique (PSP) is used to measure the model surface pressures in wind tunnel testing. In the NRC 1.5 m blowdown wind tunnel, the testing time is limited between 10 to 100 sec, depending on the mass flow rate and the tunnel geometry (2D or 3D test section).
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Optical measurements of fluctuating temperatures in a supersonic turbulent flow using one- and two-photon, laser-induced fluorescence [PDF]
A laser-induced fluorescence technique was developed that provides a practical means of nonintrusively measuring the instantaneous temperatures in low-temperature turbulent flows.
Gross, K. P., Mckenzie, R. L.
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Shockwave/Boundary-Layer Interaction Studies Performed in the NASA Langley 20-Inch Mach 6 Air Tunnel [PDF]
This paper highlights results from a collaborative study performed by The University of Tennessee Space Institute (UTSI) and NASA Langley Research Center on the Shockwave/Boundary-Layer Interaction (SWBLI) generated by a cylindrical protuberance on a ...
Bathel, Brett F. +9 more
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Cruise aerodynamics of USB nacelle/wing geometric variations [PDF]
Experimental results are presented on aerodynamic effects of geometric variations in upper surface blown nacelle configurations at high speed cruise conditions.
Braden, J. A. +2 more
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Method for static divergence analysis of sting-mounted wind tunnel models [PDF]
, 2005 Occurrence of static divergence will result in a catastrophic failure of wind tunnel models supported13; on sting or other types of support . The report presents an analysis method that can be used to design and/or13; verify the design of a model-balance-
Sundaramurthy, H
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Measured and predicted shock shapes for AFE configuration at Mach 6 in air and in CF4 [PDF]
Shock shapes and stand-off distances were obtained for the Aeroassist Flight Experiment configuration from Mach 6 tests in air and in CF4. Results were plotted for an angle-of attack range from -10 to 10 degrees and comparisons were made at selected ...
Franks, Alan M., Wells, William L.
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A study of pressure control for a blowdown wind tunnel
, 1950 http://archive.org/details ...
Kanaga, F. N., Rice, D. B.
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A survey of the three-dimensional high Reynolds number transonic wind tunnel [PDF]
The facilities for aerodynamic testing of airplane models at transonic speeds and high Reynolds numbers are surveyed. The need for high Reynolds number testing is reviewed, using some experimental results.
Aoki, T., Sawada, H., Takashima, K.
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