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Preliminary Investigation of Certain Laminar-Flow Airfoils for Application at High Speeds and Reynolds Numbers (1939)
NASA Technical Reports Server (NTRS) · leaf 13
56 .028 -20 > b it- 48 .024 -20 0 20 40 60 80 100 … Sect/on lift coetfic/e t-" Angle of attack, cc fdeg.) cm Figure 6.- N.A.C.A. 1412-34 airfoil cnNASA Technical Reports Server (NTRS)
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