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Airfoils for Light Transport Aircraft
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English
Abstract
This paper presents data from tests in a two-dimensional pressurized wind tunnel of two new wing sections suitable for light transport aircraft, and a NACA 633-418 airfoil. The two new airfoils had maximum thickness/chord ratios of 18% and 21% and they were designed to achieve improved high lift and low drag by exploiting considerable aft loading and blunt trailing edges.
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Citation
Poole, R. and Teeling, P., "Airfoils for Light Transport Aircraft," SAE Technical Paper 810576, 1981, https://doi.org/10.4271/810576.Also In
References
- Abbott I.H. Von Doenhoff A.E. “Theory of Wing Sections” Dover Publications, Inc. New York 1958
- Braslow A.L. Knox E.C. “Simplified Method for Determination of Critical Height of Distributed Roughness Particles for Boundary Layer Transition at Mach Numbers from 0 to 5. ” NACA TN 4363 1958
- Ohman L.H. “The NAE High Reynolds Number 15 in. × 60 in. Two-Dimensional Test Facility, Part 1. General Information. ” Lab. Tech. Report LTR-HA-4 1970