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- An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: Static longitudinal stability and control characteristics at a Mach number of 1.59
- Report presenting an investigation in the 4- by 4-foot supersonic tunnel to determine the static longitudinal stability and control characteristics of a supersonic aircraft configuration at a Mach number of 1.59. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.
- Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925
- Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.
- The Rolling Effectiveness of Wing-Tip Ailerons as Determined by Rocket-Powered Test Vehicles and Linear Supersonic Theory
- Report presenting testing of the rolling effectiveness and drag of half-delta wing-tip ailerons on rectangular and tapered wings sweptback 0 and 45 degrees for a range of Mach numbers. The rolling effectiveness was relatively uniform across the Mach number range and was lower at subsonic speeds and higher at supersonic speeds than the partial-span plain ailerons.
- Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered
- Report presenting the longitudinal and lateral characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at lift coefficient 0.25 and Mach number 1.5. The investigation occurred over a range of sideslip angles. The results indicated that the longitudinal characteristics were essentially unaffected by Reynolds number or the sideslip angles investigated.
- Longitudinal Stability and Control Characteristics at High Subsonic Speeds of Two Models of a Transonic Research Airplane With Wings and Horizontal Tails of Aspect Ratios 4.2 and 2
- Report discussing an investigation of two transonic research airplane models at a range of Mach numbers and Reynolds numbers. The main difference between the models was the aspect ratio of the horizontal tail. Results regarding the stability, control, incremental horizontal-tail characteristics, downwash, horizontal-tail load, stability factors, and a tailless configuration are provided.
- Longitudinal-stability characteristics of the Northrop X-4 airplane (USAF No. 46-677)
- Report presenting the results from several recent flights on the Northrop X-4 No. 2 airplane, including the longitudinal stability characteristics over a range of Mach numbers in straight and accelerated flight and the short-period longitudinal-oscillation characteristics.
- Altitude performance characteristics of turbojet-engine tail-pipe burner with variable-area exhaust nozzle using several fuel systems and flame holders
- From Introduction: "The performance of several tail-pipe burners with fixed area exhaust nozzles is reported in references 1 to 4, and the performance of an NACA-designed tail-pipe burner with a variable-area exhaust nozzle is reported in reference 5. Operational characteristics of the tail-pipe burner are also discussed."
- The Damping in Roll of Rocket-Powered Test Vehicles Having Rectangular Wings With NACA 65-006 and Symmetrical Double-Wedge Airfoil Sections of Aspect Ratio 4.5
- Report presenting a free-flight investigation of two rocket-powered model configurations to determine the damping in roll. The model had rectangular wings of 4.5 aspect ratio and were the same except for the airfoil sections. Results regarding rolling velocity and total-drag coefficient are provided.
- On the Particular Integrals of the Prandtl-Busemann Iteration Equations for the Flow of a Compressible Fluid
- "The particular integrals of the second-order and third-order Prandtl-Busemann iteration equations for the flow of a compressible fluid are obtained by means of the method in which the complex conjugate variables are utilized as the independent variables of the analysis. The assumption is made that the Prandtl-Glauert solution of the linearized or first-order iteration equation for the two-dimensional flow of a compressible fluid is known. The forms of the particular integrals, derived for subsonic flow, are readily adapted to supersonic flows with only a change in sign of one of the parameters of the problem" (p. 909).
- Investigation of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Modified Chance Vought XF7U-1 Airplane. TED No. NACA DE 311
- "An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 0.057-scale model of the modified Chance Vought XF7U-1 airplane. The primary change in the design from that previously tested was a revision of the twin vertical tails. Tests were also made to determine the effect of installation of external wing tanks" (p. 1).
- Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Abrupt Pitching Maneuvers at Approximately 20,000 Feet
- "Time histories are presented of horizontal-tail loads, elevator loads, and deformations on a jet-powered bomber during abrupt pitching maneuvers at a pressure altitude of approximately 20,000 feet. The normal and pitching accelerations measured varied from -0.90b to 3.41g and from -0.73 to 0.80 radian per second per second (sic), respectively, with a Mach number variation of from 0.40 to o.75. The maximum horizontal-tail load measured was 17,250 pounds down. The maximum elevator load was 1900 pounds up. The stabilizer twisted a maximum of 0.76 degrees leading edge down at the tip. The greatest fuselage deflection at the tail was about 1.7 inches down" (p. 1).
- Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control
- Through theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude stabilization system with proportional control for certain nonlinear pitching-moment variations and autopilot adjustments.
- The occurrence of plutonium in nature
- Plutonium has been chemically separated from seven different ores and the ratios of plutonium to uranium determined. This ratio was found to be fairly constant in pitchblende and monazite ores, in which the uranium content varied from 50% t o 0.24%, and substantially less in carnotite and fergusonite.
- 'Fission' of Medium Weight Elements
- The fission reaction has been observed with high energy accelerator projectiles for elements as light as tantalum but has not been reported for medium weight elements. The present note presents evidence for the occurrence of reactions which are probably most properly described by the term 'fission' and which seem to occur with very small yield throughout the region where this type of reaction is only slightly exoergic or even endoergic with respect to mass balance. In the course of detailed investigation of the spallation of copper and the variation of the product yields with energy of the bombarding particle the threshold for formation of radioactive Cl{sup 38} (38-minute half-life) from elemental studied. The energetically most economical way in which Cl{sup 38} might be spallation reactions is by emission from the bombarded copper nucleus of nucleons in groups such as alpha-particles instead of single nucleons 0 The energetic requirements for the reaction Cu{sup 63}(p,pn6a)Cl{sup 38}, in which the maximum number of alpha-particles are emitted, include (1) the mass difference between the reactants and the products and (2) the excitation energy which the alpha-particles must have in order to pass over the coulombic barrier, Since the reaction is endoergic with respect to atomic masses, about 50 Mev must be supplied by the impinging proton to make up the mass difference. If the alpha-particles are considered as coming out consecutively, a value of about 50 Mev can be obtained for the coulombic requirement and thus the threshold for this spallation reaction is roughly 100 Mev.
- A Report on the Safety Aspects of the Homogeneous Reactor Experiment
- No Description Available.
- CHEMICAL PROPERTIES OF URANIUM HYDRIDE
- No Description Available.
- Lecture Notes Health Physics Training Lectures, 1948-1949
- No Description Available.
- Decontamination and Corrosion Resistance Properties of Selected Laboratory Surfaces
- This report presents decontamination and corrosion resistance data on various industrial materials tested on a laboratory scale to aid in the section of materials for the construction and maintenance of radiochemical laboratories at Oak Ridge National Laboratory.
- Physical properties of Hanford metal waste
- The Hanford metal wastes were divided into four categories: supernate - the liquid waste; hard sludge - dense agglomerates of poorly defined crystalline carbonates approximating the hardness of soft blackboard chalk; soft sludge - an easily slurried semi-solid consisting chiefly of needle-like phosphates; and recombined sludge - a representative sample of the solid wastes as received from Hanford, shown to be a mixture of hard and soft sludges in the ratio 2/3 by weight. The density of supernate, in the temperature range 24 to 74/sup 0/C, varied from 1.130 to 1.103 g/ml. Hard sludge density averaged 3.0 g/ml and that of soft sludge averaged 1.84 g/ml. The consistency, or apparent viscosity, as a function of temperature, shear rate, and solids content was measured individually on slurries of recombined, soft, and hard sludges using supernate as the suspending medium. Settling rates were also run on these 3 slurries as a function of solids content.
- Recovery of Nitric Acid in the Tributyl Phosphate Process for Uranium Recovery. Part 2.
- Report discussing study on recovery of nitric acid in the uranium recovery process. The behavior of chloride ions and tributyl phophate is noted, and the quality of recycled nitric acid was tested. Stainless steel in the nitric acid recovery system was evaluated for corrosion.
- Operations incidents
- No Description Available.
- P-10 air monitor design criteria
- This HAPO report documents the design criteria for the P-10 air monitor at the 300 Area. Minimum reliable readings and accompanying remarks document testing of four different monitors.
- A rapid, simple method for the determination of the radon content of water
- The historical approach to the separation of radon from water is liberation of the radon from the sample by boiling under vacuum in the presence of a strong acid; flushing the liberated radon, with an inert gas, into an ionization chamber or an alpha proportional counters and measuring the collected activity. Such an analysis requires a manipulation time of approximately one hour, a waiting period of two to three hours before measurement to allow transitory equilibrium to be reached, and finally a measurement time, resulting in 4 to 6 hours for one analysis. In addition, specialized equipment including a vacuum train is required. If it is desired to count the alpha particles from radon and its daughters in a proportional counter, absorption trains to remove all oxygen, a poor counting gas, are required. The method presented herein requires only 20--25 minutes for a complete analysis and except for the beta counter utilizes standard laboratory equipment.
- 100 Areas technical activities report -- Engineering, February, 1950
- This report covers work done by the Physical Chemistry Group and the Pile Engineering Groups. Subjects covered are as follows: metal exposure details; slug corrosion details; pile control -- thimble removal study; Van Stone flange corrosion details; process tube corrosion details; carbon dioxide experiment; graphite sampling; special pile measurements; routine pile measurements; 105 technical laboratories; P-10; boiling studies; pile annealing studies; gas tube experiment; thermal conductivity and electrical resistivity; x-ray diffraction studies; and stored energy.
- Serial Reports on Start-Up Experiments. No. 1 The Hot Rod Experiment
- The purpose of this new series of reports is to present in roughly finished form the results of the various start-up experiments on the BNL reactor as soon as the analysis of the experimental data is completed.