The effects of camber and leading-edge-flap deflection on the pres¬sure pulsations on thin rigid airfoils at Mach numbers from 0.5 to 1.0 have been investigated. The tests included variations in camber cor-responding to design lift coefficients of 0, 0.2, and 0.5, as well as variations in deflection of a 15-percent-chord leading-edge flap from 0° to -15° on a 6-percent-thick NACA 64A-series airfoil. The high pulsations associated with leading-edge flow separation on the basic airfoil were significantly reduced either by use of camber or by suitable deflection of a 15-percent-chord leading-edge flap. The optimum camber or flap deflection were dependent on Mach number and normal-force coefficient. Comparison of the data for the basic 64A006 section used in these tests with data previously obtained for the 65A006 section revealed significantly lower pressure pulsations 'for the 65A006 airfoil.
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