From Summary: "Pressure distributions and force characteristics have been determined for a body of revolution consisting of a fineness ratio 5.75, circular-arc, ogival nose tangent to a cylindrical afterbody for an angle-of-attack range of 0 degrees to 35.5 degrees. The free-stream Mach number was 1.98 and the free-stream Reynolds number was approximately 0.5 x 10 sup 6, based on body diameter. Comparison of the theoretical and experimental pressure distributions shows that for zero lift, either slender-body theory or higher-order theories yield results which are in good agreement with experiment."

Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.

Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist. Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.

From Summary: "The transonic similarity rules have been applied to the correlation of experimental data for a series of 22 rectangular wings having symmetrical NACA 63A-series sections, aspect ratios from 1/2 to 6, and thicknesses from 2 to 10 percent. The data were obtained by use of the transonic bump technique over a Mach number range from 0.40 to 1.10, corresponding to a Reynolds number range from 1.25 to 2.05 million. The results show that it is possible to correlate experimental data throughout the subsonic, transonic, and moderate supersonic regimes by using the transonic similarity parameters in forms which are consistent with the Prandtl-Glauert rule of linearized theory."

The high-work-output turbine had an experimental efficiency of 0.830 at the design point and a maximum efficiency of 0.857. The downstream stator was effective in providing axial flow out of the turbine for almost the whole range of turbine operation.

Report presenting the design details of two transpiration-cooled strut-supported turbine rotor blades. One design uses a sintered blade shell while the other uses a wire blade shell. Ideal coolant flows were found for an effective gas temperature of 1425 degrees Fahrenheit, a coolant temperature of 180 degrees Fahrenheit, and a shell temperature of 600 degrees Fahrenheit.

Report discussing the stability and control characteristics and drag of a canard or tail-first configuration explored using the free-fall method. Information about the basic flight characteristics, experimental coefficients, zero-lift drag configurations, and longitudinal stability and trim characteristics is provided.

Stress-rupture data for four heat-resisting alloys are analyzed according to equations of the theory of rate processes. A method for determining the four parameters of structure and composition is demonstrated and the four parameters are determined for each of the alloys: forged S816, cast S816, cast S590, and cast Vitallium. It is concluded that parameters can be determined for an alloy provided sufficient reliable experimental data are available.

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.

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 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 an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects 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).

Theoretical calculations of specific impulse to determine the separate effects of increasing the combustion-chamber pressure and the nozzle expansion ratio on the performance of the propellants, hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine and AN-F-58 fuel - white fuming nitric acid (95 percent). The results indicate that an increase in specific impulse obtainable with an increase in combustion-chamber pressure is almost entirely caused by the increased expansion ratio through the nozzle.

Report presenting an investigation to determine the effects of external ribs, or load carrying fences, on the rolling effectiveness and drag on swept wings of two different stiffnesses. The primary effect of adding fences was a decrease in torsional flexibility and an increase in zero-lift rolling effectiveness. The aerodynamic effects on zero-lift rolling effectiveness due to adding fences are negligible.

An analytical investigation of the effects of fuel density and heating value on the cruising range of a ram-jet airplane was made. Results indicate that with present-day knowledge of chemical fuels, neither very high nor very low fuel densities have any advantages for long-range flight. Of the fuels investigated, the borohydrides and metallic boron have the greatest range potential. Aluminum and aluminum hydrocarbon slurries were inferior to pure hydrocarbon fuel and boron-hydrocarbon slurries were superior on a range basis. It was concluded that the practical difficulties associated with the use of liquid hydrogen fuel cannot be justified on a range basis.

A study of the effect of fuel-orifice diameter on the performance of heptane-oxygen rocket engines with single-element injectors. Five engines with a range of thrust were tested with parallel-sheet, triplet, and parallel-jet injectors. Decreasing the fuel-orifice diameter was found to increase the performance for a fixed chamber length. Results regarding injector performance and a comparison of experimental and analytical results are provided.

The effects of inlet-air-flow distortions on the performance of the J65-B-3 turbojet engine were determined over a range of altitudes from 15,000 to 50,000 feet at a flight Mach number of 0.8. Radial inlet-air-flow distortions apparently do not affect the radial distribution of pressure after the first few compressor stages, while the circumferential inlet-air-flow distortion carried completely through the engine. For the distortions investigated, at rated exhaust-gas temperature and fixed-area exhaust-nozzle operation, the primary effect of the radial inlet-air-flow distortions was to reduce the engine air flow, and the primary effect of the circumferential distortion was to impose a temperature profile on the turbine, both resulting in reduction of thrust.

Report presenting the effects of nacelle location on the zero-lift drag of 45 degree sweptback wing-body combinations with boattail and cylindrical afterbodies at a range of Mach and Reynolds numbers. The nacelles were located at three different areas and the afterbody shape was also altered by replacing the boattail afterbody with a cylinder. Results regarding faired curves of the variations of total drag, base drag, and fin drag coefficients, and applicability of the transonic area rule are 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 to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. An evaluation of the basic redesign of the compressor and 11 additional modifications are examined.

Report discussing an investigation of the effect of spanwise aileron location on the rolling effectiveness of plain faired ailerons on untapered wing plan forms with designated sweep, airfoil sections, and aspect ratio using rocket-propelled test vehicles. Drag data is also presented for all configurations tested. Spanwise aileron location was found to have little effect on the effectiveness of the aileron on an unswept wing plan form.

Memorandum presenting tests in the 9-inch supersonic tunnel of three bomb or store shapes without fins and with two sets of cruciform fins. Measurements of normal force, chord force, and pitching moment were made; analyses of the effects of angle of attack and Reynolds number on these qualities and also upon center-of-pressure position and fin effectiveness are presented.

Report presenting a wind-tunnel investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and a wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. The effects of wing height on the longitudinal characteristics of the model were small.