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Reynolds Number Effects on the Stability and Control Characteristics of a Supersonic TransportA High Speed Civil Transport (HSCT) configuration was tested in the National Transonic Facility at the NASA Langley Research Center as part of NASA's High Speed Research Program. A series of tests included longitudinal and lateral/directional studies at transonic and low speed, high-lift conditions across a range of Reynolds numbers from that available in conventional wind tunnels to near flight conditions. Results presented focus on Reynolds number sensitivities of the stability and control characteristics at Mach 0.30 and 0.95 for a complete HSCT aircraft configuration including empennage. The angle of attack where the pitching-moment departure occurred increased with higher Reynolds numbers for both the landing and transonic configurations. The stabilizer effectiveness increased with Reynolds number for both configurations. The directional stability also increased with Reynolds number for both configurations. The landing configuration without forebody chines exhibited a large yawing-moment departure at high angles of attack and zero sideslip that varied with increasing Reynolds numbers. This departure characteristic nearly disappeared when forebody chines were added. The landing configuration's rudder effectiveness also exhibited sensitivities to changes in Reynolds number.
Document ID
20020023445
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Owens, L. R.
(NASA Langley Research Center Hampton, VA United States)
Wahls, R. A.
(NASA Langley Research Center Hampton, VA United States)
Elzey, M. B.
(Boeing Commercial Airplane Group Seattle, WA United States)
Hamner, M. P.
(LeaTech, LLC Baltimore, MD United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2002
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA Paper 2002-0417
Meeting Information
Meeting: 40th AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 14, 2002
End Date: January 17, 2002
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
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