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Profile design for an advanced-technology airfoil for general aviation aircraftA profile from the NASA General Aviation Whitcomb series and NACA profiles are used as a starting point in designing an advanced airfoil for general aviation aircraft. Potential theory pressure distribution calculations, together with boundary layer calculations, permit a decrease in the null moment and an optimization of the lift characteristics of the wing. Trailing edge flap design is also improved. Wind tunnel tests are used to compare the conventional profiles, the NASA profile, and the improved design.
Document ID
19780024111
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Welte, D. (NASA Headquarters Washington, DC United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-75323
PAPER-77-027
Report Number: NASA-TM-75323
Report Number: PAPER-77-027
Accession Number
78N32054
Funding Number(s)
CONTRACT_GRANT: NASW-3199
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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