An investigation of flow characteristics at Mach number 4.04 over 6- and 9-percent-thick symmetrical circular-arc airfoils having 30-percent-chord trailing-edge flaps

摘要

Section data obtained from wind-tunnel tests at Mach number 4.04 and Reynolds numbers of about 5.0 times 10 to the 6th power and 8.4 times 10 to the 6th power are presented for 6- and 9-percent-thick symmetrical circular-arc airfoils with 30 percent chord trailing-edge flaps. Pressure distributions, Schlieren photographs, and force and moment coefficients are included.