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NASA low- and medium-speed airfoil development
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TLDR
The status of NASA low and medium speed airfoil research is discussed in this article, where the authors present the application of NASA-developed airfoils to general aviation aircraft.Abstract:
The status of NASA low and medium speed airfoil research is discussed. Effects of airfoil thickness-chord ratios varying from 9 percent to 21 percent on the section characteristics for a design lift coefficient of 0.40 are presented for the initial low speed family of airfoils. Also, modifications to the 17-percent low-speed airfoil to reduce the pitching-moment coefficient and to the 21-percent low speed airfoil results are shown for two new medium speed airfoils with thickness ratios of 13 percent and 17 percent and design-lift coefficients of 0.30. Applications of NASA-developed airfoils to general aviation aircraft are summarized.read more
Citations
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ReportDOI
Design and experimental results for the S809 airfoil
TL;DR: In this article, a 21-percent-thick laminar flow airfoil, the S809, for horizontal-axis wind-turbine applications, has been designed and analyzed theoretically and verified experimentally in the lowturbulence wind tunnel of the Delft University of Technology Low Speed Laboratory, The Netherlands.
Journal ArticleDOI
Natural-laminar-flow airfoil for general-aviation applications
TL;DR: A natural-Iamina r-flow airfoil, the NLF(1)-0115, has been recently designed for general-aviation aircraft at the NASA Langley Research Center as mentioned in this paper.
Design and experimental results for a flapped natural-laminar-flow airfoil for general aviation applications
TL;DR: In this paper, a natural-laminar flow airfoil for general aviation applications, the NLF(1)-0416, was designed and analyzed theoretically and verified experimentally in the Langley Low-Turbulence Pressure Tunnel.
NASA supercritical airfoils: A matrix of family-related airfoils
TL;DR: Some of the airfoil design guidelines are discussed, and coordinates of a matrix of family related supercritical airfoils ranging from thicknesses of 2 to 18 percent and over a design lift coefficient range from 0 to 1.0 are presented.
Journal ArticleDOI
Low-Reynolds-Number Effects in Passive Stall Control Using Sinusoidal Leading Edges
TL;DR: In this paper, the application of a sinusoidal leading edge to the design of micro air vehicles was investigated, and the results depend strongly on the aspect ratio of the leading edge.
References
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BookDOI
Supercritical Wing Sections II
Low-speed aerodynamic characteristics of a 13-percent-thick airfoil section designed for general aviation applications
TL;DR: In this article, wind-tunnel tests were conducted to determine the low-speed section characteristics of a 13-percent-thick airfoil designed for general aviation applications.
Proceedings ArticleDOI
A Fowler Flap System for a High-Performance General Aviation Airfoil
W. H. Wentz,H. C. Seetharam +1 more
TL;DR: In this paper, a two-dimensional wind-tunnel evaluation of two Fowler flap configurations on the new GA(W)-1 airfoil was conducted, and a C sub L max of 3.8 was achieved.
Development of a Fowler flap system for a high performance general aviation airfoil
W. H. Wentz,H. C. Seetharam +1 more
TL;DR: In this article, a two-dimensional wind-tunnel evaluation of two Fowler flap configurations on the new GA(W)-1 airfoil was conducted, and a C sub L max of 3.8 was achieved.