High-Speed Investigation of Skin Wrinkles on Two NACA Airfoils
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY
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The affects on the aerodynamic characteristics of skin wrinkles on the forward part of the upper surface of two NACA airfoils, the NACA 66, 1-115 and 23015 sections, at speeds up to Mach number 0.73 were investigated and the results compared with those obtained for the same two airfoils under smooth conditions. No appreciable change in normal-force or pitching-moment characteristics was caused by the wrinkle on an airfoil section. The drag was greater for the wrinkled configuration than for the smooth one.