Memorandum presenting tests conducted to determine the flight characteristics of an F-86F airplane equipped with an area-suction-type boundary-layer control installation on the trailing-edge flaps. Measurements were made of the lift, drag, and engine bleed-air requirements. Results regarding the aerodynamic characteristics as well as some miscellaneous characteristics are provided.

Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.

Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.

From Summary: "Motion pictures at camera speeds up to 3000 frames per second were taken of the combustion of liquid oxygen and gasoline in a 100-pound-thrust rocket engine. The engine consisted of thin contour and injection plates clamped between two clear plastic sheets forming a two-dimensional engine with a view of the entire combustion chamber and nozzle. A photographic investigation was made of the effect of seven methods of propellant injection on the uniformity of combustion. From the photographs, it was found that the flame front extended almost to the faces of the injectors with most of the injection methods, all the injection systems resulted in a considerable nonuniformity of combustion, and luminosity rapidly decreased in the divergent part of the nozzle."

"The spin and recovery characteristics of the Curtiss-Wright XP-87 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape, are presented in this report. The characteristics were estimated rather than determined by model tests because the XP-87 dimensional and mass characteristics were considered to be noncritical and because data were available from model tests of several similar airplanes. The study indicated that the recovery characteristics of the airplane will be satisfactory for all loadings if the controls are reversed fully and rapidly" (p. 1).

Report presenting an investigation studying the effects of compressibility on the internal-flow characteristics of an NACA 1-series cowling-spinner combination equipped with a dual-rotation propeller at Mach numbers up to 0.8. Two propellers were examined, one with a sealed propeller-spinner juncture and one with a raised-platform-airfoil shaped juncture. The propeller was not found to have appreciable compressibility effects on the impact pressures when operating at design cruise blade angle.

Memorandum presenting low-lift drag and longitudinal trim data for two versions of an interceptor-type airplane, the second of which had a slimmer nose and a thinner tail than the first. Data are presented for three models (complete, wingless, and horizontal tailless) of the first version, and from one model (complete configuration) of the second version. Results regarding longitudinal trim, drag, longitudinal stability, and flutter and buffet are provided.

Memorandum presenting the aerodynamic loading on delta wings at supersonic speeds, which was studied primarily to determine the coupling and nonlinear interference effects between the pressures due to angle of attack and due to thickness. Results regarding span loadings and lift coefficients, pressure distributions due to thickness, pressure distributions due to angle of attack and interference pressures produced by thickness, and Reynolds number effects are provided.

Memorandum presenting an investigation of the effects of compressibility on the forces, pitching moments, and surface pressures on a wing-nacelle combination. The leading edge of the wing was swept back 37.25 degrees and the nacelle was a body of revolution with a fineness ratio of 6.5. The effects of compressibility on the surface pressures and on the drag of a body of revolution similar to the nacelle were also determined.

Memorandum presenting an investigation of the location of transition from laminar to turbulent flow in the boundary layer on two bodies of revolution at zero angle of attack in a low-turbulence wind tunnel. One body was a prolate spheroid of fineness ratio 9.0 made out of aluminum and the other was a modified prolate spheroid of fineness ratio 7.5 made out of steel and covered with fiberglass and resin.

Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.

Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.

Report presenting an investigation in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. The surface of the airfoil that was tested had a lot of waves and irregularities, but the theoretically predicted stabilizing effect of area suction on a smooth flat plate was still observed.

Report presenting a theoretical analysis of the air flow through the blade coolant passages in an air-cooled turbine rotor. The simultaneous effects of area change, compressibility, wall friction, heat transfer, and rotation were included.

From Summary: "An investigation was conducted on a 12-cylinder V-type liquid-cooled aircraft engine of 1710-cubic-inch displacement to determine the minimum specific fuel consumption at constant cruising engine speed and compression ratios of 6.65, 7.93, and 9.68. At each compression ratio, the effect.of the following variables was investigated at manifold pressures of 28, 34, 40, and 50 inches of mercury absolute: temperature of the inlet-air to the auxiliary-stage supercharger, fuel-air ratio, and spark advance. Standard sea-level atmospheric pressure was maintained at the auxiliary-stage supercharger inlet and the exhaust pressure was atmospheric."

Report presenting tests at low speeds in the low turbulence pressure tunnel and the stability tunnel in order to determine the extent of any resulting oscillations of a model mounted with freedom in yaw and to demonstrate the extent to which directional fluctuations in an air stream can be responsible for the oscillations.

Report presenting aerodynamic and icing investigations conducted in the icing research tunnel on a model of a turbojet-engine nacelle with a long straight air inlet in order to provide basic design criteria for hot-gas blowback systems. The most uniform temperature distribution was obtained with a bleedback of 4.4 percent at a gas temperature of 1000 degrees Fahrenheit and resulted in an average dry-air-temperature rise of 46 degrees Fahrenheit.

Report presenting tests to evaluate the usefulness of available theory for the calculation of lift-curve slope and center of pressure of low-aspect-ratio, triangular, and rectangular cruciform wings in combination with a long slender body. Tests were made over a range of Mach and Reynolds numbers based on model length.

Report presenting tests of an NACA 4-(5)(08)-03 two-blade propeller in the 8-foot high-speed tunnel for blade angles of 45 and 60 degrees extending the Mach number range from that of previous tests of the propeller up to Mach number 0.913. When the forward speed was increased from a low value to a forward Mach number of 0.90, the loss in peak efficiency was found to be not more than 47 percent.

Report presenting an investigation to determine flight behavior after ejection from a bomb bay of several dynamically scaled bluff internal stores for a range of Mach numbers and altitudes. The trajectories of all of the stores were smooth, but the pitching motions of the stores were greatly affected by the close vicinity of the bomb bay. Types of stores explored included WADC stores, flared-cylinder stores, and cylindrical stores.

"The stability of systems containing a heat source is examined from the energy point of view. Rayleigh's criterion is derived. In the case of a flame, it is found that Rayleigh's criterion must be modified slightly if the specific-heat ratios of the burned and unburned gases are different" (p. 1).

Report presenting a free-flight investigation to determine normal-force and hinge-moment characteristics of a half-diamond tip control on a diamond wing with 60 degree sweptback leading edges and 30 sweptforward tailing edges for a range of Mach numbers. Results regarding control hinge moments, control normal force, and total normal force are provided.

Report presenting an investigation of a swept, rectangular, supersonic scoop inlet designed to have low external drag at the design Mach number of 2.7. The inlet was tested with two simulated fuselages with circular and rectangular cross sections. Results regarding shadow photographs, pressure recovery, wedge effects, drag, boundary-layer control, Mach number distribution in diffuser, wedge loads, aspect-ratio effects, and applicability of results are provided.

Report presenting wind-tunnel testing to determine the low-speed lift, drag, and pitching-moment characteristics of a 40 degree sweptback wing with high-lift and stall-control flaps and a fuselage with a fineness ratio of 10.2 to 1. Low, medium, and high-wing-fuselage combinations were tested at high Reynolds numbers. Results regarding the high-lift and stall-control flaps and wing-fuselage combinations are provided.