Report presenting testing to determine the interference effects of various sting-support configurations on the base pressure and foredrag characteristics of a wing-fuselage combination with a turbulent boundary layer. The primary variable investigated was the length of the constant-diameter portion of a sting support. Results regarding the base-pressure interference and foredrag interference are provided.

Report presenting an investigation of the effects of sideslip on the aerodynamic loading characteristics of a 45 degree sweptback wing of aspect ratio 4 for a range of angles of attack, angles of sideslip, and Mach numbers. The load distributions, root bending-moment coefficient, and rolling moment due to sidestep were explored.

Report presenting a method for extending to higher Mach numbers the region of low drag attainable for wing-body combinations by the use of the transonic area rule. To a good approximation, the drag depends only on the longitudinal distributions of area and moments of area about the vertical plane of symmetry parallel to the free-stream direction. The experimental results confirm the theory in that the zero-lift wave drag of a wing-body configuration over a range of low supersonic Mach numbers.

Report presenting a theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase. Factors considered in the investigation included effects of control-system parameters, effects of limitations on control deflection and rate of control deflection, effects of initial tracking errors, effects of nonlinear variations in drag and lift with angle of attack and Mach number, effects of nonlinear variations in pitching moment with angle of attack, effect of variations in interceptor forward velocity, and the effect of a normal acceleration limiter on the system performance.

Report presenting wind-tunnel tests at a range of Mach numbers to measure the static longitudinal stability characteristics of a semispan wing-fuselage-tail model having a wing with 45 degrees of sweepback. The wing had an aspect ratio of 5.5 and had NACA 64A010 sections normal to the quarter-chord line. The center of pressure of the wing-fuselage combination moved forward as the wing began to stall, and a tail in the higher positions produced additional stalling moments due to high effective downwash.

Report presenting a wind-tunnel investigation to determine the low-speed aerodynamic characteristics of an airplane arrangement with an unswept horizontal tail and a triangular wing with an aspect ratio of 3 equipped with partial-span single-slotted flaps and plain ailerons. The effects of flap deflection on the longitudinal characteristics were investigated at several tail positions. Results indicated taht satisfactory longitudinal stability up to a lift coefficient of 1.35 was attained only when the tail was below the wing-chord plane.