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Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 230. (1936)
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-.4 -8 Corrected for tunnel-wall effect. , i,.—^-i 1 1—- .2 A .6 ,8 1.0 1.2 1.4 1.6 1.8 ' -4 -.2 0 -8 -4 0 4 8 12. 16 20 24 28 32 i Lift coefficient ck Angle of attack, oe (degrees) >->• Figure l.-RAjCA. 23006.airfoil wNASA Technical Reports Server (NTRS)
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