Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics of boundary-layer control are provided.

Report presenting an investigation on a model of a 40 degree swept-wing fighter airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight testing. The effects of high-lift and stall control devices, horizontal-tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated.

Memorandum presenting an investigation conducted to determine the effect on the low-speed resistance and spray characteristics and static transverse stability of a modification which extended the bow of a scale model of a nose-inlet transonic seaplane configuration. The investigation was made with and without tip floats. The change was found to result in a 50-percent reduction in the hump resistance, increased engine-inlet clearance, reduced low-speed spray and hull-side flow, and acceptable spray and resistance at 25-percent overload.

Report presenting results of evaluation flights of F-86 series aircraft equipped with two types of boundary-layer control, which differed significantly in regards to the type of lift increment produced. The report presents the comments of 16 Air Force, Navy, contractor, and NACA pilots as to the reasons for their choice of minimum, comfortable approach speed on the several configurations tested.

Report presenting an investigation in the high-speed tunnel at Mach numbers from 0.80 to 0.92 to determine the effects of fuselage shape on the aerodynamic characteristics of a model with low and high wing arrangements. Results regarding longitudinal stability characteristics and lateral stability characteristics of the different component combinations are provided.