Influence of a canard-type control surface on the internal and external performance characteristics of nacelle-mounted supersonic diffusers (conical centerbody) at a rearward body station for a Mach number of 2.0

L. J. Obery, H. S. Krasnow
naca-rm-e52f16
Aug 1952


The effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers (conical centerbody type) and on the engine-body interference drag were investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.0, angles of attack from 0 to 10 degrees, control-surface deflection angles from 0 to 9 and one-half degrees, and at Reynolds number of approximately 1.5 X 10(exp 6) based on inlet diameter.

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