NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Application of FLEET Velocimetry in the NASA Langley 0.3-meter Transonic Cryogenic Tunnel Femtosecond laser electronic excitation and tagging (FLEET) velocimetry is demonstrated in a large-scale transonic cryogenic wind tunnel. Test conditions include total pressures, total temperatures, and Mach numbers ranging from 15 to 58 psia, 200 to 295 K, and 0.2 to 0.75, respectively. Freestream velocity measurements exhibit accuracies within 1 percent and precisions better than 1 m/s. The measured velocities adhere closely to isentropic flow theory over the domain of temperatures and pressures that were tested. Additional velocity measurements are made within the tunnel boundary layer; virtual trajectories traced out by the FLEET signal are indicative of the characteristic turbulent behavior in this region of the flow, where the unsteadiness increases demonstrably as the wall is approached. Mean velocities taken within the boundary layer are in agreement with theoretical velocity profiles, though the fluctuating velocities exhibit a greater deviation from theoretical predictions.
Document ID
20160006092
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Burns, Ross A.
(NASA Langley Research Center Hampton, VA, United States)
Danehy, Paul M.
(NASA Langley Research Center Hampton, VA, United States)
Halls, Benjamin R.
(Spectral Energies, LLC Dayton, OH, United States)
Jiang, Naibo
(Spectral Energies, LLC Dayton, OH, United States)
Date Acquired
May 13, 2016
Publication Date
June 22, 2015
Subject Category
Instrumentation And Photography
Report/Patent Number
NF1676L-20421
Meeting Information
Meeting: AIAA Aviation 2015
Location: Dallas, TX
Country: United States
Start Date: June 22, 2015
End Date: June 26, 2015
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNX14CL74P
WBS: WBS 432938.09.01.07.90
Distribution Limits
Public
Copyright
Public Use Permitted.
No Preview Available