Linearized Theory of Wind Tunnel Interference at Transonic Speed
The Journal of the Japan Society of Aeronautical Engineering, 1956 It has been proved that a linearized theory is consistent for three dimensional lifting case at sonic and nearly sonic speeds and is also applicable to a nonlifting case in the field of Mach number nearly one which has boundaries at finite distances.
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An Ultra-Fast TSP on a CNT Heating Layer for Unsteady Temperature and Heat Flux Measurements in Subsonic Flows. [PDF]
Sensors (Basel), 2022 Bitter M +4 more
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Evaluation of moire techniques for wind tunnel metrology [PDF]
The development of a moire technique suitable for the analysis of object deflections in a cryogenically cooled, transonic wind tunnel is described. The operating environment for the wind tunnel has a temperature range of 77 to 3390 k, pressure to 91390 ...
Harding, K. G., Harris, J. S.
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High Reynolds number test of a NACA 651-213, a equals 0.5 airfoil at transonic speeds [PDF]
Wind-Tunnel tests were conducted in the Lockheed-Georgia Company's compressible flow facility to determine the transonic two-dimensional aerodynamic characteristics of a NACA 65 sub 1-213 a = 0.50 airfoil. The results are correlated with data obtained in
Blackwell, J. A., Jr. +2 more
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HIGH-LIFT BEHAVIOUR OF HALF-MODELS AT FLIGHT REYNOLDS NUMBERS
TASK Quarterly, 2006 A peniche is designed to offset a half-span aircraft model from the wind tunnel wall boundary layer. This strategy of model mounting results in large influence on the measured aerodynamic coefficients, compared with full-span data.
PIOTR DOERFFER, OSKAR SZULC
doaj
Effect of tip winglet position on tip flow and noise of axial flow fan. [PDF]
Heliyon, 2023 Diao L +5 more
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Streamlining the walls of an empty two-dimensional flexible-walled test section [PDF]
The techniques used to find aerodynamically straight wall contours in a test section of a transonic wind tunnel are discussed.
Cook, I. D. +2 more
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Comparison of the NASA Common Research Model European Transonic Wind Tunnel Test Data to NASA Test Data [PDF]
Experimental aerodynamic investigations of the NASA Common Research Model have been conducted in the NASA Langley National Transonic Facility, the NASA Ames 11-ft wind tunnel, and the European Transonic Wind Tunnel.
Quest, Jurgen +2 more
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Practical Fast-Response Anodized-Aluminum Pressure-Sensitive Paint Using Chemical Adsorption Luminophore as Optical Unsteady Pressure Sensor. [PDF]
Sensors (Basel), 2022 Oka Y +5 more
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Calibration of the Langley 16-foot transonic tunnel with test section air removal [PDF]
The Langley 16-foot transonic tunnel with test section air removal (plenum suction) was calibrated to a Mach number of 1.3. The results of the calibration, including the effects of slot shape modifications, test section wall divergence, and water vapor ...
Corson, B. W., Jr. +2 more
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