An investigation of flow characteristics at Mach number 4.04 over 6- and 9-percent-thick

Edward F. Ulmann, Douglas R. Lord
naca-rm-l51d30
Jul 1951


symmetrical circular-arc airfoils having 30-percent-chord trailing-edge flaps 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.

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