Compilation of data obtained in flight with six pursuit type airplanes embodying typical conventional and low drag airfoils; these flight data, which cover range of Mach numbers from 0.15 to 0.72 and of Reynolds numbers from 4,400,000 to 19,500,000, are analyzed, together with pertinent model and airfoil data obtained in several wind tunnels.
Effect of Mach and Reynolds numbers on maximum lift coefficient
Nat Advisory Committee Aeronautics -- Tech Note
1946
20 pages
19 Supp Sheets, Bibliography
Report
Englisch
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