From Wing Thickness: "A brief review of the effect of wing thickness and thickness distribution on the high-speed performance and stability characteristics of a representative configuration is presented."

From Summary: "In order to provide a basis for judging the relative importance of wing failure by fatigue and by single intense gusts, an analysis of wing life for normal cruising flight was made based on data on the frequency of atmospheric gusts. The independent variables considered in the analysis included stress-concentration factor, stress-load relation, wing loading, design and cruising speeds, design gust velocity, and airplane size. Several methods for estimating fatigue life from gust frequencies are discussed."

From Introduction: "The purpose of this report is to present the results of the analysis and to compare them with the experimental results of the transonic turbine."

Methods of conversion of UF4 to U3O8 by fusion with ammonium oxalate dihydrate and other salts are described.

Abstract:"The creep resistance of various uranium binary alloys was investigated at 1500 and 1800 F in vacuum. Tests were made on alloys of uranium with beryllium, columbium, molybdenum, tantalum, titanium, and zirconium and on molybdenum-UO2 composites. Of the alloys examined, those of the uranium-molybdenum system exhibited the best creep resistance. At 1500 F, creep rates of about 0.005%/hr were produced in uranium-molybdenum alloys by a stress of 2500 psi and, at 1800 F, similar creep rates were obtained in composites of 90 wt % molybdenum-10 wt % UO2 by a stress of 12,000 psi."

Abstract: "The uranium content of badly contaminated uranium solutions may be determined quickly using visual comparison methods to an accuracy of [...]. This accuracy may be considerably improved by employing the fluorimeter herein described. Interfering ions and their removal using liquid-liquid extractions are considered."

"The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model" (p. 1).

The operation of the Fast Reactor is considered in terms of normal equilibrium conditions and normal shut-down. The proposed loading, control rod adjustment and subsequent "floating" operation are discussed. Safety devices and interlocks are described. Temperature and reactivity changes are examined with respect to various system failures, phase changes, and "flashing" of the reactor. Slow changes due to faulty slug cooling are also considered. The calculations were initially based upon 10 kw operation. Performance tests of the mercury system now indicate that 20-kw operation may be feasible.

From abstract: "Electrical measurements have been made on CaB6, SrB6, BaB6, YB2, YB4, YB6, and YB12 for the purpose of testing models of the electronic structure of the boron atoms in the four boride types represented. The compounds CaB6, SrB6, and BaB6 were found to be semiconductors. The Hall coefficients of YB4 was also measured, but could not be interpreted because the free electron theory does not provide a theoretical value for comparison with experiment. The results are in agreement with the models proposed."

Memorandum presenting a rocket-propelled model of a representative 35 degree sweptback wing airplane design at high subsonic Mach numbers to investigate the possibility of the existence of coupled longitudinal and lateral motions. The data indicate the existence of sustained longitudinal motions of appreciable amplitude forced by lateral oscillations. The longitudinal motions had twice the frequency of the lateral oscillations and are shown to be the result of aerodynamic moments due to sideslip and inertial cross coupling.

"A considerable weight reduction in the turbine wheel of an aircraft gas turbine is attained through the use of high-aspect-ratio rotor blading. An experimental investigation was made to compare the performance of a turbine of conservative aerodynamic design having shrouded rotor blades with an aspect ratio of 4.48 with that obtained from both a shrouded and an unshrouded rotor design with aspect ratio of 2.24. The use of high-aspect-ratio rotor blades had a negligible effect on the turbine efficiency" (p. 1).

"A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).

Report presenting the results of testing of bodies and wing-body combinations by the free-fall method in order to provide information about drag characteristics of airplanes and their component parts at transonic speeds. Two models with a fineness-ratio-12 body of revolution with 45 degree sweptback wings located at different positions were dropped and equipped with improved drag measuring instrumentation and pressure measuring orifices on the portion of the body expected to be influenced by the presence of the wing. Results regarding pressure data and drag data are provided.

Report presenting an investigation of a series of 16-inch-diameter ramjet engine in free flight in order to determine the performance of ramjet units in flight at supersonic speeds and to study methods for improving the performance. Results regarding the telemeter data recorded by ground stations, static pressures, variation of altitude with time after release, variation of flight velocities, and fuel-air ratio are provided. Partial failure of the measuring equipment prevented a complete evaluation of engine performance.

The remodeling, fabrication, and instrumentation of a high vacuum system are described. The faults encountered with the old system and their solution are outlined. Tests were made on diffusion pump oils and on the reduction of pump oil back diffusion. The measurement of high vacuum pressures by a cold cathode ionization gage at various points on a vacuum system are discussed.

The fission and spallation reactions caused in uranium by bombardment with high energy protons (340 to 350 Mev) were investigated. The reaction products were separated from the target by chemical processes and identified by their radioactive properties. The relative yields of the observed fission products were measured, and the results plotted as a function of mass number. Several of the spallation products were identified and their yields estimated.

"A 49 degree swept-wing complete model equipped for high-pressure blowing full span at two chordwise locations at the leading edge of a full-span wing and over a half-span flap has been tested in the Langley full-scale tunnel to determine the effectiveness of blowing at the leading edge as a supplementary leading-edge stall control at high lift coefficients." The effect of blowing on the lift characteristics, pitching-moment characteristics, and drag characteristics of this particular model is described.

Report presenting an investigation to determine the high-speed performance and static longitudinal stability and control characteristics of a model of the Lockheed YP-80A airplane. High-speed aerodynamic characteristics are presented for speeds up to Mach number 0.96. Results regarding the scale effects, longitudinal stability, and longitudinal-control effectiveness are provided.

Aerodynamic and icing investigations of internal water-inertia separation inlets designed to prevent automatically entrance of large quantities of water into a turbojet engine in icing conditions was conducted on a one-half scale model. A simplified analytical approach to the design of internal water-inertia separation inlets is included. Results show that in order to be effective in preventing screen and guide-vane icing for an inlet of this type, a ram-pressure recovery of 75 percent was attained at design inlet-velocity ratio in an icing condition. For nonicing operation, ram-pressure recovery is comparable to direct-ram inlet.

Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models cooled with lithium hydride are provided.

Report presenting testing of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. The models were tested in the ceramic-heated jet at a Mach number of 2, a stagnation temperature of 4,000 degrees Fahrenheit, and a stagnation pressure of 105 lb/sq. in. abs. Lithium hydride offers significant cooling for the materials while magnesium shows a slight cooling.

Report presenting the results of two runs made with liquid diborane and hydrogen peroxide in a small-scale rocket engine. The first run was very erratic and modifications were made to the testing apparatus and procedures for the second run. In the second run, the combustion started immediately and continued smoothly for 12 seconds of operation.

"The mean strain rate in turbulent shear flow must tend to make the structure anisotropic in all parts of the spectrum. It is argued here, however, that if the spectral energy transfer process destroys orientation, the Kolmogoroff notion of local isotropy can still be justified in spectral regions where the local transfer time is shorter than the characteristics time of the gross shear strain" (p. 1).

Results of previous toroid tests with 28 micro 1600 fired ThO2 spheres are analyzed. Four possible explanations for the essentially zero attack rates are offered and discussed: peculiar motion of toroids or some unknown wall effect; rotational hydrodynamic forces cushioning the particle impact; the bed was not in suspension and not sliding over the walls of the toroid; round particles are not as erosive to oxide film surface as sharp pointed particles.