Donald L. Loving, Claude V. Williams
The data presented herein are the first results of pressure measurements obtained on a fuselage and a 45 degree sweptback wing-fuselage combination at transonic speeds in the slotted test section of the Langley 8-foot high-speed tunnel. This test was part of a systematic investigation of varying amounts of sweepback on wings suitable for transonic flight. Pressure distributions were obtained at five spanwise stations on the wing and along six meridians on the fuselage.
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