Influence of a canard-type control surface on flow field in vicinity of symmetrical fuselage at Mach numbers 1.8 and 2.0

George A. Wise, Murray Dryer
Jul 1952

An experimental investigation of the flow field downstream of a canard-type control surface and in the vicinity of a symmetrical body was conducted in the NACA Lewis 8- by 6-foot supersonic tunnel at Mach numbers of 1.8 and 2.0. Local stagnation pressures and flow deflection angles were measured 2.14 mean aerodynamic chord lengths downstream of the trailing edge of the control surface.

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