Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.

Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.

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.

Memorandum presenting an investigation to determine the feasibility of increasing the specific weight flow of a transonic axial-flow compressor inlet stage by decreasing the hub-tip ratio. The current phase of the investigation was conducted to determine the blade-element and the overall performance of the complete stage. Results regarding the overall performance, blade-element performance, and stator-blade-element performance are provided.

Memorandum presenting an investigation of the performances of two annular diffuser designs applicable to turbojet afterburner installations to determine the effectiveness of injection and suction boundary-layer controls. Results regarding inlet measurements, flow observations, static-pressure distributions, downstream velocity distributions, and mean performance coefficients are provided.

Report presenting a flight program using the Northrop X-4 semitailless airplane to investigate the effect on the longitudinal and lateral stability and control of thickened elevons with trailing-edge thickness one-half the control-hinge-station thickness. The investigation consisted of speed runs, wind-up turns, abrupt rudder-fixed rolls, and longitudinal pulses between a range of Mach numbers.

Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.

Report presenting the steady-state performance of the YJ73-GE-3 turbojet engine in an altitude test chamber for a range of exhaust-nozzle areas, simulated altitudes, and Mach numbers. A method of performance calculation based on engine pumping characteristics is provided. Results regarding performance maps, pumping characteristics and performance prediction, thrust correlation, effect of inlet temperature on performance, calculated performance from pumping characteristics, and altitude-ignition characteristics are provided.

Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.

Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are provided.

A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.

"A tip section of a delta wing having an NACA 0004-65 airfoil section and a 600 leading-edge sweepback was equipped with a porous leading-edge section through which hot gas was bled for anti-icing. Heating rates for anti-icing were determined for a wide range of icing conditions. The effects of gas flow through the porous leading-edge section on airfoil pressure distribution and drag in dry air were investigated" (p. 1).

Memorandum presenting an investigation of a flight version of the NACA heated-wire liquid-water-content instrument, which was constructed and flight tested in natural icing conditions. Data obtained simultaneously with rotting multicylinders indicated that reliable flight measurements of liquid-water content could be made with the heated-wire instrument.

Report presenting testing to determine the longitudinal stability characteristics of the TX-17, the "Short Seven", and the TX-21 special weapons. Dynamic and static stability data are provided for a range of Mach numbers and stagnation-pressure levels.

Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.

Memorandum presenting an investigation to determine the altitude performance characteristics of the YJ73-GE-3 turbojet engine in an altitude chamber. The component performance was determined at two positions of the inlet guide vanes over a range of engine speeds, exhaust-nozzle areas, and flight conditions. Results regarding compressor performance, combustor performance, turbine performance, and altitude performance of components at rated conditions 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 an investigation of the effect of longitudinal body fences on the performance of a top-inlet-fuselage combination in the 8- by 6-foot supersonic wind tunnel. The investigation was conducted at a range of Mach numbers, angles of attack, and a range of inlet mass-flow ratios. The thrust-minus-drag of the top-inlet configuration with fences was higher than the bottom-inlet configuration without fences over most of the range, with the reverse being true at all lift coefficients at Mach 2.0 and higher lift at Mach 1.8.

Report presents information about free-flight rocket-propelled model testing to determine the effect of some wing geometry variables on low lift drag at a range of Mach numbers. Results regarding the effect of airfoil section, wing nose droop and nose flaps, plan form, and wing vertical position are provided.

Report presenting pressure distributions calculated for some symmetrical wing-body combinations at zero lift. Of particular interest is the effect of indenting the body on the distribution of pressure over the wing.

Report presenting limited flight measurements made in order to investigate the effect of dynamic vibration absorbers on the structural response of a Lockheed F-80A airplane during buffeting. The results were obtained by comparison of data with and without the absorbers operating through use of electrical frequency-analysis techniques.

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.

"A two-dimensional investigation utilizing pressure-distribution measurements and schileren photographs has been made of the flow and force characteristics of slab-sided airfoils of 2-percent thickness at transonic Mach numbers. The airfoils had various combinations of elliptically shaped leading and trailing edges from a fineness ratio of 0 to 10. The aerodynamic characteristics and an analysis of the flow past the models are presented" (p. 1).