Wind-tunnel investigation at subsonic and low transonic speeds of the effects of aileron span and spanwise location on the rolling characteristics of a test vehicle with three untapered 45 degree sweptback wings

Harold S. Johnson
Apr 1951

A wind-tunnel investigation was made through a Mach number range of 0.30 to about 0.94 to determine the rolling characteristics of a three-winged free-flight type of test vehicle having untappered 45 degree sweptback wings of NACA 65A009 airfoil sections and equipped with 0.20-chord ailerons having various spans and spanwise locations. The aspect ratio based on the area of two wings was 3.7.

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