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Static aerodynamic characteristics of a typical single-engine low-wing general aviation design for an angle-of-attack range of -8 deg to 90 degStatic force data obtained at the NASA Ames Research Center 12 foot Pressure Tunnel are presented in plotted form for a 1/7 scale, single-engine, low-wing general aviation airplane model. The configurations tested included the basic airplane, various airfoil shapes, tail designs, fuselage strakes and fuselage modifications as well as airplane components. The test conditions included an angle-of-attack and sideslip range of -8 to 90 and -10 to 30 degrees, respectively, at a Mach number of 0.2 for Reynolds numbers of 288,000 and 3,450,000. The data are presented without analysis.
Document ID
19780022105
Document Type
Contractor Report (CR)
Authors
Bihrle, W., Jr. (Bihrle Applied Research, Inc. Jericho, NY, United States)
Barnhart, B. (Bihrle Applied Research, Inc. Jericho, NY, United States)
Pantason, P. (Bihrle Applied Research, Inc. Jericho, NY, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1978
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-CR-2971
Funding Number(s)
CONTRACT_GRANT: NAS1-14849
PROJECT: RTOP 505-10-1307
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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