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Design and Experimental Results for a Low-Speed, Flapped, Slotted, Natural-Laminar-Flow AirfoilA 12.91-percent-thick, flapped, slotted, natural-laminar-flow (SNLF) airfoil, the S702, intended for a low-speed, fixed-wing aircraft has been designed and analyzed theoretically and verified experimentally in The Pennsylvania State University Low-Speed, Low- Turbulence Wind Tunnel. The two primary objectives of high maximum lift, insensitive to roughness, and low profile drag have been achieved. The airfoil exhibits a sharp stall that is less abrupt than the stalls of earlier SNLF airfoils, which meets the design objective. The constraint on the pitching moment has been satisfied. Comparisons of the theoretical and experimental results show reasonably good agreement overall, given the complexity of the configuration.
Document ID
20220014964
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Dan M. Somers
(Airfoils (United States) Bellefonte, Pennsylvania, United States)
Mark D. Maughmer
(Airfoils (United States) Bellefonte, Pennsylvania, United States)
Date Acquired
October 4, 2022
Publication Date
December 1, 2022
Subject Category
Aerodynamics
Report/Patent Number
NASA/CR-20220014964
Funding Number(s)
CONTRACT_GRANT: NNX17AJ95A
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Keywords
slotted airfoil
natural laminar flow
University Leadership Innitiative
Transonic Truss-Braced Wing
drag reduction
subsonic
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