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Tests of three tapered airfoils based on the N.A.C.A. 2200, the N.A.C.A.-M6, and the Clark Y sections (1934)
NASA Technical Reports Server (NTRS) · leaf 10
Angle of attaok, a (degrees) Figure 3." Airfoil: Tapered Clark T. R.I.: 3,170,000 Sire: 5- (mean chord) x 30" ^ Vel. (ft./eec.): 68.9 Press, (st'n'd. atm.): 30.8 Dates; 1 6 33, 4 5 33 Where tested! Ll.A.L. Tests: V.D.T. 943, 1017 Results corrected for tunnel-wall effect.NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
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