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Wind tunnel results of the low-speed NLF(1)-0414F airfoilThe 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.
Document ID
19900003225
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Murri, Daniel G. (NASA Langley Research Center Hampton, VA., United States)
Mcghee, Robert J. (NASA Langley Research Center Hampton, VA., United States)
Jordan, Frank L., Jr. (NASA Langley Research Center Hampton, VA., United States)
Davis, Patrick J. (PRC Kentron, Inc., Hampton VA., United States)
Viken, Jeffrey K. (Mandex, Inc., Falls Church VA., United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1987
Publication Information
Publication: Research in Natural Laminar Flow and Laminar-Flow Control, Part 3
Subject Category
Aerodynamics
Accession Number
90N12541
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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