Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.

Report presenting an investigation of a conservatively designed experimental cold-air turbine with and without a shroud band on the rotor blades. The tip of the rotor blade was oriented toward the tangential direction so that the adverse effect of blade-tip scraping would not be appreciable. The efficiency for the unshrouded-rotor configuration was about one point higher than for the shrouded rotor.

Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and operational requirements are provided.

Report presenting an investigation of combustion oscillations using white fuming nitric acid and a hydrocarbon fuel in a 1000-pound-thrust rocket engine. Results regarding rotary oscillation shown by 40,000-frame-per-second photographs, oscillations recorded by streak photography, ion gap traces, pressure measurements, and plastic chamber erosion are provided.

"Aerodynamic data have been obtained for a 45-degree sweptback wing-body-canopy configuration at transonic speeds with the canopy placed on the body so that the cross-sectional area of the canopy approximately filled the concave portion of the basic wing-body cross-sectional-area distribution curve (design location) and with the canopy placed 0.0614 of the body length forward of the design location. Data have also been obtained for the basic wing-body combination. Placing the canopy in the rear position significantly reduced the drag of the configuration at transonic speeds, increased the lift, and did not appreciably affect the slope of the pitching-moment curve" (p. 1).

Report presenting the results of force and moment tests at Mach numbers from 3.0 to 6.3 on bodies of revolution of fineness ratios from 5 to 10 and on flat-bottom bodies of fineness ratio 10 along with theoretical predictions for these bodies. Testing included eight cone and cone-cylinder models, six nose-cylinder models, and three flat-bottom bodies.

Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings of aspect ratios 2 and 4 at Mach numbers of 1.45 and 1.97. The investigation includes some comparison of the effects of Reynolds number and of thickening the wing root sections on the loading.

Memorandum presenting an investigation of two-dimensional, supersonic cascade-type inlets at a free-stream Mach number of 3.11. Two cascade-type inlets utilizing different methods of internal-flow compression were designed and tested. Results regarding the cascade inlet and stepped-cascade inlet are provided.

Report presenting an investigation of stores on the Douglas D-558-II research airplane in the wind tunnel and in flight using various store configurations. The drag measured for all store configurations was high, from two to three times the free-air drag estimated for the store and pylon. Results regarding longitudinal characteristics and lateral characteristics are provided.

"Measurement of average skin-friction coefficients have been made on six rocket-powered free-flight models by using the boundary-layer rake technique. The model configuration was the NACA RM-10, a 12.2-fineness-ratio parabolic body of revolution with a flat base. Measurements were made over a Mach number range from 1 to 3.7, a Reynolds number range 40 x 10(exp 6) to 170 x 10(exp 6) based on length to the measurement station, and with aerodynamic heating conditions varying from strong skin heating to strong skin cooling" (p. 1).

Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.

Report presenting an analytical and experimental investigation of the effects of cooling-air impeller performance on turbojet-engine performance at 70 and 100 percent of rated engine speed. Analysis indicated that the impeller performance has little effect on engine performance at rated engine speed for the coolant flows considered. Results regarding the impeller total-pressure ratio and cooling air available with compressor bleed are provided.

Report presenting an investigation of air-launched ram jets using models with double-cone inlets with a design free-stream Mach number of 2.4. Drag data are presented in the form of cowl pressure drag, additive drag, internal drag, base drag, and total drag. Mass-flow ratios and ram-jet total-temperature ratios are also provided.

Report presenting an evaluation of the internal performance characteristics of several plug-type nozzles over a range of pressure ratios from 1.5 to 30. Results regarding isentropic plug nozzles, conical plug nozzles, the effect of throat and throat-approach section on performance, and air-flow parameter are provided.

Report presenting an investigation of three axial-flow-compressor inlet stages with a hub-tip diameter ratio of 0.5 to determine whether high pressure ratios can be obtained by means of high turning with highly cambered subsonic types of blading and the effectiveness of radial gradients of energy addition in reducing the deceleration across the rotor tip and thus relieving the effect of high tip loading. Results regarding the overall stage performance, diffusion factor, element performance, and stage discharge flow distribution are provided.

Air-launched firings of eight T-40 rockets have been made. An average total impulse of 22,870 pound-seconds was observed for four of the rounds mounted in cone-cylinder vehicles. Maximum velocities of over 5000 feet per second were observed for two of the rounds with approximately 70-pound pay loads.

Report presenting the results of an investigation of the internal dynamics of a ramjet engine and the steady-state and dynamic performance characteristics of a number of ramjet controls. Three types of engine control systems were investigated: (1) shock positioning, (2) direct control of diffuser-exit pressure, and (3) an optimalizing control designed to obtain peak pressure recovery from the diffuser. Results regarding the engine steady-state performance, engine dynamics, and controls investigations are provided.

Report presenting an investigation to measure the effect of base bleed on the base pressure, lift, drag, and pitching moment of a 10-percent-thick blunt-base airfoil model. Small holes near the lower surface near the trailing edge into the base region were used to create base bleed. The drag was reduced as a result of the bleed holes.

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.

Report presenting an investigation to determine the zero-lift rolling effectiveness of all-movable sweptback horizontal tail fins mounted behind a notched delta wing at a constant angle of differential incidence of 7 degree per fin. Two models, one with a stiff wing and one with a flexible wing, were tested in free flight over a range of Mach numbers. The rolling effectiveness was about the same magnitude at subsonic and supersonic speeds for both models.

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 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.

From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."

Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.