Results obtained from wind tunnel tests on a 21% thick supercritical airfoil capable of sustaining long runs of laminar flow on both surfaces are presented. The measured drag levels are superior to those of any model previously tested in this facility and are comparable to classical NACA and modern NASA NLF airfoils.
Analysis of Experimental Data for a 21% Thick Natural Laminar Flow Airfoil, NAE68-060-21:1
1985
56 pages
Report
Keine Angabe
Englisch
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