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Flight Test Investigations of a Wing Designed for Natural Laminar Flow
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English
Abstract
Full scale flight tests of a wing designed for natural laminar flow (NLF) have provided insight into the aerodynamic characteristics of the airfoil used (NLF(1)-0414F), and into the effects of transition location on airfoil lift, drag, pitching moment and overall aircraft performance. Results of these tests help answer questions pertaining to the development of aircraft using NLF airfoils such as the one tested. These data also provide comparisons of predictions based on computational and wind tunnel test methods. Instrumentation methods used to gather data during these tests include flush mounted airfoil pressure orifices, hot film anemometers and a wing mounted integrating wake rake.
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Authors
Citation
Befus, J., Nelson, E., Ellis, D., and Latas, J., "Flight Test Investigations of a Wing Designed for Natural Laminar Flow," SAE Technical Paper 871044, 1987, https://doi.org/10.4271/871044.Also In
References
- Viken Jeffrey K. “Aerodynamic Design Considerations and Theoretical Results for a High Reynolds Number Natural Laminar Flow Airfoil” Master's Thesis George Washington University January 1983
- McGhee Robert J. Viken Jeffrey K. Pfenninger W. Beasely William D. Harvey William D. “Experimental Results for a Flapped Natural-Laminar-Flow Airfoil with High Lift/Drag Ratio”. NASA 1984
- Silverstien A. Katzoff S. “A Simplified Method for Determining Wing Profile Drag in Flight” 7 7 May 1940 295 301
- Holmes Bruce J. “Flight Experiences with Laminar Flow” NASA Conference Publication 2413 1985