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Two-dimensional wind-tunnel tests of a NASA supercritical airfoil with various high-lift systems. Volume 1: Data analysisHigh-lift systems for a NASA, 9.3%, method for calculating the viscous flow about two-dimensional multicomponent airfoils was evaluated by comparing its predictions with test data. High-lift systems derived from supercritical airfoils were compared in terms of performance to high-lift systems derived from conventional airfoils. The high-lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: a single-slotted flap; a double-slotted flap and a leading-edge slat; and a triple-slotted flap and a leading-edge slat. Agreement between theoretical predictions and experimental results are also discussed.
Document ID
19800003804
Document Type
Contractor Report (CR)
Authors
Omar, E. (Boeing Co. Seattle, WA, United States)
Zierten, T. (Boeing Co. Seattle, WA, United States)
Mahal, A. (Boeing Co. Seattle, WA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1977
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-CR-2214
D6-41063-1-VOL-1
Funding Number(s)
CONTRACT_GRANT: NAS1-10824
PROJECT: RTOP 760-64-60-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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