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Wind-tunnel investigation of basic aerodynamic characteristics of a supercritical-wing research airplane configurationTransonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic characteristics of a 0.087 scale model of a supercritical wing research airplane configuration at Mach numbers from 0.25 to 1.30. The investigation included tests to determine the basic longitudinal aerodynamic characteristics, the lateral-directional aerodynamic characteristics for sideslip angles of 0 deg and + or - 2.5 deg, and the effects of Reynolds number and aeroelasticity.
Document ID
19780016135
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Dennis W Bartlett (Langley Research Center Hampton, Virginia, United States)
Richard J Re (Langley Research Center Hampton, Virginia, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-2470
L-7979
Report Number: NASA-TM-X-2470
Report Number: L-7979
Accession Number
78N24078
Funding Number(s)
PROJECT: RTOP 742-73-01-14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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