The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil

Joseph W. Cleary, George L. Stevens
naca-rm-a51j11
Dec 1951


The effects of a systematic variation of trailing-edge thickness of a symmetrical, circular-arc airfoil on the aerodynamic force, moment, base-pressure, and wake fluctuations have been investigated using the transonic-bump testing technique. The investigation of the effects of one boattail modification was also made.

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