Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45 degree sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds numbers

Albert L. Braslow, Gene J. Bingham
naca-rm-l54b18a
Apr 1054


An investigation has been made in the Langley low-turbulence pressure tunnel at low subsonic speeds through a range of Reynolds number from approximately 1.0 X 10(exp 6) to 7.6 X 10(exp 6) to study the effects of body indentation in accordance with the transonic area rule on the zero-lift drag of a transonic body in combination with a 45 degree sweptback wing having an aspect ratio of 4, taper ratio of 0.3 and NACA 65A006 airfoil sections.

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