Preliminary investigation at a Mach number of 1.9 and a Reynolds number of 2,200,000 of three ailerons applicable to the Bell XS-2 airplane design

James C. Sivells, William D. Conner
naca-rm-l8d02
May 1948


A 42.7 degree sweptback tapered wing with three types of ailerons was tested in the Langley 9- by 12-inch supersonic blowdown tunnel at a Mach number of 1.9 and a Reynolds number of 2,200.000. The wing geometry was essentially that of the XS-2 airplane. One of the ailerons had the basic airfoil contour which was an 8-percent-thick symmetrical biconvex section with a trailing-edge angle of 19.8 degrees.

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