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Supersonic Inlet Test for a Quiet Supersonic Transport Technology Demonstrator in the NASA Glenn 8- by 6-Foot Supersonic Wind TunnelNASA funded the preliminary design of a flight demonstrator aircraft with a greatly reduced sonic boom signature to enable supersonic flight over land. In 2017, two tests were performed at the NASA Glenn Research Center 8- by 6-foot Supersonic Wind Tunnel, an aerodynamic stability/control test and an inlet performance test. The inlet was unique due to the location on the vehicle, located on the top centerline near the rear of the aircraft. Test data provided a validation and performance dataset for engine integration on the demonstrator vehicle. The subject of this report is the subsonic and supersonic performance data collected for the centerline top-mounted inlet.
Document ID
20180006432
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Castner, Raymond
(NASA Glenn Research Center Cleveland, OH, United States)
Simerly, Stephanie
(NASA Glenn Research Center Cleveland, OH, United States)
Rankin, Michael
(Lockheed Martin Corp. Palmdale, CA, United States)
Date Acquired
October 18, 2018
Publication Date
August 1, 2018
Subject Category
Aeronautics (General)
Report/Patent Number
AIAA Paper 2018-2850
NASA/TM-2018-219956
E-19567
GRC-E-DAA-TN59194
Meeting Information
Meeting: AIAA Space Forum
Location: Atlanta, GA
Country: United States
Start Date: June 25, 2018
End Date: June 29, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 339442.04.03
Distribution Limits
Public
Copyright
Public Use Permitted.
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