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A two-dlmensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-series airfoils with thickness ratios of 4, 6, and 9 percent has been conducted in the Langley airfoil test apparatus at transonic Mach numbers between 0.8 and 1.25. The Reynolds number range for these tests varied from 2.6 million to 2.8 million. As was expected, the aerfoils exhibited a smooth transition in force coefficients from a Mach number of 1.0 to the values obtained at the higher speeds. Lift

Author

Karkhia Lorissa

Language

EN