NDLI: Wind tunnel results of the low-speed nlf(1)-0414f airfoil

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Wind tunnel results of the low-speed nlf(1)-0414f airfoil

Content Provider	NASA Technical Reports Server (NTRS)
Author	Jordan Jr., Frank L. Davis, Patrick J. McGhee, Robert J. Murri, Daniel G. Viken, Jeffrey K.
Copyright Year	1987
Description	The large performance gains predicted for the Natural Laminar Flow (NLF)(1)-0414F airfoil were demonstrated in two-dimensional airfoil tests and in wind tunnel tests conducted with a full scale modified Cessna 210. The performance gains result from maintaining extensive areas of natural laminar flow, and were verified by flight tests conducted with the modified Cessna. The lift, stability, and control characteristics of the Cessna were found to be essentially unchanged when boundary layer transition was fixed near the wing leading edge. These characteristics are very desirable from a safety and certification view where premature boundary layer transition (due to insect contamination, etc.) must be considered. The leading edge modifications were found to enhance the roll damping of the Cessna at the stall, and were therefore considered effective in improving the stall/departure resistance. Also, the modifications were found to be responsible for only minor performance penalties.
File Size	8548169
Page Count	24
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19900003225
Archival Resource Key	ark:/13960/t23c0xx29
Language	English
Publisher Date	1987-12-01
Access Restriction	Open
Subject Keyword	Aerodynamics Flight Tests Damping Aerodynamic Drag Turbulent Flow Low Speed Two Dimensional Flow Lift Laminar Flow Laminar Flow Airfoils Wind Tunnel Tests Boundary Layer Transition Control Stability Leading Edges Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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