From Summary: "As part of a study of means of airspeed measurement at transonic speeds the use of static orifices located ahead of the wing tip has been investigated for possible application to service or research airspeed installations. The local static pressure and local Mach number have been measured at a distance of 1 tip chord ahead of the wing tip of a model of a swept-wing fighter airplane at true Mach numbers between 0.7 and 1.08 by the NACA wing-flow method. All measurements were made at or near zero lift. The local Mach number was found to be essentially equal to the true Mach numbers less than about 0.90."

Report presenting an experimental investigation of pyramidal, wedge-like bodies as devices for delaying separation of a turbulent boundary layer. Within certain limits, effective boundary-layer control was obtainable with wedges of different geometry, but the drag of the wedges was high, making it desirable to keep their size to a minimum. Greater maximum lift was obtainable by placing the wedges well forward along the chord and by allowing open spaces between adjacent wedges.

Report presenting a compilation of free-spinning model results of investigations of the spin and recovery characteristics of 12 flying-wing and unconventional-type designs. Dimensional data, mass data, and three-view drawings of the models that correspond to each of the 12 airplane designs are provided. Results regarding erect spins, inverted spins, and spin-recovery parachutes are also provided.

Report presenting results from flight tests at transonic speeds for a canard and a conventional-tail rocket-powered model in continuous rough air. The use of an airspeed-fluctuation instrument for measuring the turbulence intensity experienced is described as well as the resulting improvement in the technique of testing rocket models in rough air. The short-period frequency was dominant in the center-of-gravity normal-acceleration response for both models.

Report presenting hydrodynamic force characteristic for three streamline bodies of revolution equipped with chine strips and with fineness ratios of 6, 9, and 12. Testing was also performed on the bodies with the chine strips removed and with the tail cones removed. Hydrodynamic resistance, pitching moment, wetted length, and height of the model above the water surface for a range of trim, load, and speed are provided.

Report presenting testing of a 60-degree delta-wing-fuselage model with a 4-percent-thick airfoil section with large leading-edge radius in the 19-foot pressure tunnel to determine the effectiveness of porous-leading-edge suction in delaying and reducing the leading-edge separation and accompanying high drag. Results regarding the delta wing, including pump power, lift, pitching moment, pressure distributions, the clipped wing, and some comments on the application of leading-edge suction to delta wings are provided.

Report presenting a rough-water landing investigation of a model of a hydro-ski seaplane design to determine the effect on the landing motions and vertical accelerations of mounting the hydro-ski on shock-absorber struts. The tests occurred at one landing trim and wave height over a range of wave length for three hydro-ski configurations. Results regarding the landings, effect of artificial stabilization, damping in trim, and reductions in vertical accelerations are provided.