Abstract
Interference pressure distribution data were obtained at M = 1.9 for the body of a flat rectangular wing-cylindrical body combination with a laminar boundary layer on the body. The results are compared with earlier experimental results obtained with a turbulent boundary layer on the body and with the linearized inviscid theory of NACA T N 2677. The experimental results agree well with theory except for viscous effects not predicted by the theory. Qualitative similarity of the shock-wave and laminar boundarylayer interaction to the two-dimensional case is noted. Body lift loading due to interference for two configurations representing missiles with wings or control surfaces near the tail is discussed.
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