Report presenting an exploration of the proposition that the structural weight of supersonic missiles should be reduced by the use of pressurized, thin-wall, glass-laminated shells. A model with this type of structure was investigated in the 8- by 6-foot supersonic wind tunnel to determine the minimum internal pressure necessary to prevent panel flutter. Results regarding the empty shell and shell containing liquid are provided.

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 an investigation of the static longitudinal-stability characteristics of a 45 degree sweptback wing-fuselage configuration with and without a sweptback horizontal tail for a range of angles of attack and Mach numbers. Special focus is given to the pitching-moment characteristics, location of the aerodynamic center, and slope of the lift-coefficient curve.

Report presenting an investigation in the transonic blowdown tunnel to determine the effects of variations in inlet lip swagger from 0 to 60 degrees on the internal-flow characteristics of an unswept semielliptical scoop-type air-inlet model without boundary-layer control. Tests were made for a range of Mach numbers and mass-flow ratios. Results regarding the flow over the fuselage nose, total-pressure recovery at inlet, flow distortions at inlet, and inlet-design considerations are presented.

Memorandum presenting the analysis of direct-connect performance data obtained with five flame holders of various gutter and can types operated in a 20-inch-diameter ramjet engine at Mach number 3, which revealed that the specific impulse of each of the flame holders was about the same. The combustion-chamber length had a marked effect on specific impulse. Results regarding flame-holder performance and effect of combustion-chamber length on flame-holder performance are provided.

"Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss" (p. 1).

This report details a study that was conducted by the U.S. Naval Air Development Center to "determine the feasibility of several airborne magnetic mine-sweeping methods. The advantages of a satisfactory airborne method are greater safety and speed than are possible with existing surface methods." The configurations and results of the double Q-sweep, the modified double-catenary sweep, and the M-sweep are examined.

Memorandum presenting tests at two supersonic speeds to obtain experimentally the aerodynamic damping characteristics of a control surface on a two-dimensional wing. The control surface had a chord of 1.67 inches and a span of 7.25 inches and was supplied in three materials with different mass, inertia, and stiffness properties. Results regarding the presentation of data and comparison with theory and comparison with control-surface data for a triangular wing are provided.

Report presenting an investigation in the high speed tunnel of three missile models with cruciform delta wings swept back 80 degrees and equipped with jet controls to determine the effectiveness of the controls when using ram or mechanically compressed air. Results regarding the rolling characteristics, static rolling-moment coefficients, static pressure, and effect of the location of the jet control are provided.

Report presenting a study to compare the maneuvering performance of a cruciform and a monowing missile. Results regarding beam riding and minimum launch range at 5000 and 50,000 feet are provided.

"Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations will for the most part apply to any type of engine-propeller combination and system of control, the only additional material required consisting of the actual engine and propeller curves for propulsion unit" (p. 241).

Report detailing an investigation of the aerodynamic characteristics of a wing-propeller combination with the propeller rotating in the wing-chord plane of a two-dimensional wing. Total static lift was measured with and without the wing for a 3-foot-diameter propeller, while the effects of a ground plane on the static lift of the wing-propeller combination were measured with a 2-foot-diameter propeller. Results regarding static testing, forward speed tests, and propeller loads are provided.

Report presenting an assessment of various inlet design philosophies assessed on the basis of recent experimental results at Mach numbers up to 5. The basic compression systems are compared for Mach 4.0 turbojet and hypersonic-cruise ramjet engines.The best-suited inlet for the Mach 4.0 turbojet engine is the combined external-plus-internal compression.

Report presenting testing of a five-stage rocket-propelled model flown to a Mach number of 15.5 and an altitude of 98,200 feet. Temperatures were measured at six stations along the inside surface of the blunted conical nose with a total angle of 29 degrees. Experimental and theoretical values were similar at the first temperature measuring station, but the experimental results became increasingly greater than the theoretical values at rearward measuring stations.

"Existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents are presented. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is included to the flow. Errors due to variations in the configuration of static-pressure vents are also presented" (p. 1).

Report presenting an investigation of transpiration cooling in a preflight jet model consisting of a double wedge of 40 degrees included angle with a porous stainless-steel specimen inserted flush with the top surface of the wedge. Nitrogen and helium were used as coolants and testing was conducted for flow rates ranging from about 0.03 to 0.30 percent of the local weight flow. The helium coolant required only about one-fourth to one-fifth the coolant flow weight as the nitrogen coolant for the same amount of heat-transfer reduction.

Report presenting a free-flight investigation of the zero-lift rolling effectiveness of air-jet spoilers on an unswept flexible wing over a range of Mach numbers. Testing was made to determine the relative effectiveness of air-jet spoilers at leading-edge and trailing-edge locations. The leading-edge jet spoiler exhibited near-zero effectiveness at transonic speeds and had a roll reversal between Mach numbers 0.93 and 1.35.

Report presenting an investigation of several combustor configurations to determine if the length of the engine could be reduced. Testing indicated that when using a highly reactive fuel in the low subsonic region of the diffuser, part of the engine length can be eliminated.

Report presenting a graphic method for determining the composition and phases within a propellant tank when liquid oxygen is pressurized with nitrogen gas and some of the calculations involved. The assumed limiting conditions are that pressurizing gas flows adiabatically from the pressure tank and that equilibrium exists in the oxygen-nitrogen system. The experiment indicates that a series dilution of the oxidant occurs when nitrogen is used as a pressurizing gas, but a barrier at the liquid-gas interface would permit the use of nitrogen.

This report includes the description and results of an experiment evaluating the amount of adhesion existing between the liquid boron oxide and various materials used in engines.

Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.

Memorandum presenting two nose inlets utilizing the boundary-layer separation ahead of a blunt body to provide a compression surface at Mach number 5.5. Results regarding the spherical-nose inlet, the planar-nose inlet, some operating characteristics, and a comparison with the single-conical-shock inlet are provided.

Report presenting an investigation to study the effects of liquid-fuel distribution on combustion performance of a single turbojet-engine combustor operating with liquid MIL-F 5624 fuel. Results regarding altitude limits and combustion efficiencies, liquid-fuel distribution, fuel state, and miscellaneous observations are provided.

This investigation was made to adapt wet-process autoradiography to metallurgical samples to obtain high resolution of segregated radioactive elements in microstructures. Results are confined to development of the technique, which was perfected to a resolution of less than 10 microns. The radioactive samples included carbon-14 carburized iron and steel, nickel-63 electroplated samples, a powder product containing nickel-63, and tungsten-185 in N-155 alloy.