UNT Libraries Government Documents Department - 92 Matching Results

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Gas Cooled Nuclear Reactor Study

Description: Study of a gas cooled reactor with design specifications providing for a source of high temperature heat to a stream of helium. This reactor, in turn, is used as a source of heat for the air stream in a gas-turbine power plant.
Date: July 31, 1956
Creator: Thompson, A. S.
Item Type: Refine your search to only Report
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A Brief Summary of Experience in Boosting Aerodynamic Research Models

Description: "Approximately 2,000 flights of rocket-propelled models have been made in which model configuration, model size, type and number of booster rockets, number of booster stages, and booster arrangements varied. A brief summary of the results obtained with some of the more unusual arrangements, descriptions of boosting hardware and techniques, and discussions of some factors responsible for the choice of these configurations are presented in this paper. The results show that unconventional boosting… more
Date: July 27, 1956
Creator: Thibodaux, Joseph G., Jr.
Item Type: Refine your search to only Report
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Crystallite Sizes of PuO_2 Powders

Description: In connection with studies of the chemical reactivity of PuO_2 to hydrofluorination, samples were examined by X-ray diffraction for crystallite size and perfection. The PuO_2 was formed by thermal decomposition of the oralate. The reactivity of this oxide, as well as that of other solid oxides is affected by the conditions of preparation. Besides the obvious influence of surface, including lattice strain and other structural irregularities in the particles. Each particle is composed of a number… more
Date: July 27, 1956
Creator: Pallmer, P. G.
Item Type: Refine your search to only Report
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Exploratory investigation at a Mach number of 5.20 of the longitudinal aerodynamic characteristics of flat-bottom bodies

Description: Report presenting an investigation at Mach number 5.20 to determine the longitudinal aerodynamic characteristics of a number of flat-bottom bodies which were investigated for possible hypersonic applications. The bodies were tested at positive and negative angles of attack to simulate flat-bottom and flat-top arrangements.
Date: July 27, 1956
Creator: Lange, Roy H.
Item Type: Refine your search to only Report
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Exploratory Investigation of a Helicopter Pressure-Jet System on the Langley Helicopter Test Tower

Description: Report presenting an investigation of a helicopter pressure-jet system. The effects of tip speed, fuel-air ratio, and pressure ratio on the propulsive characteristics of the pressure-jet system have been determined for a range of tip seeds, blade-root stagnation-pressure ratios, and fuel-air ratios. Results regarding tip-burner specific propulsive horsepower, propulsive horsepower per unit mean duct area, tip-burner specific fuel consumption, ratio of propulsive horsepower to equivalent air hor… more
Date: July 27, 1956
Creator: Makofski, Robert A. & Shivers, James P.
Item Type: Refine your search to only Report
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Low-speed wind-tunnel results for a thin aspect-ratio-1.85 pointed-wing-fuselage model with double slotted flaps

Description: Report presenting a wind-tunnel investigation at low speeds of a thin aspect-ratio-1.85 pointed-wing-fuselage model with double slotted flaps, including the effects of a straight and delta horizontal tail on the static longitudinal stability and the effect of a delta vertical tail on the static lateral stability. Results regarding the longitudinal aerodynamic characteristics and lateral stability characteristics are provided.
Date: July 27, 1956
Creator: Brown, Albert E.
Item Type: Refine your search to only Report
open access

The Suppression of Chlorine Volatilization in Nitric Acid Distillation

Description: Description of Invention: Chloride-induced corrosion is a serious problem in the Purex acid recovery operation and in the evaporative concentration of process streams and waste solutions. In the case of Purex acid recovery, it has been shown that trace chloride will volatilize with the nitric acid and reflux in the acid fractionator, thus causing especially severe corrosion at that point. These traces of chloride may enter the process form several sources, i.e., as an impurity in the technical … more
Date: July 27, 1956
Creator: Moore, R. L.
Item Type: Refine your search to only Report
open access

Emission Rate of Fission Products from a Hole in the Cladding of a Reactor Fuel Element

Description: It is assumed that when a hole appears in the cladding of a reactor fuel tube the fission products in the space between the fuel and the cladding will diffuse towards the hole. There they are swept away by the flow of steam past the hole. The process of diffusion is assumed to be governed by the ordinary diffusion equation with the boundary condition that the density of the fission products is zero at the surface of the hole. The diffusion equation is solved for the case of steady-state emissio… more
Date: July 26, 1956
Creator: Helstrom, Carl W.
Item Type: Refine your search to only Report
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Investigation of unsteady flow past four NACA 6-percent-thick airfoil sections

Description: Report presenting an investigation of the intensity of root-mean-square pressure pulsations and root-mean-square normal-force-coefficient fluctuations conducted on two high-lift airfoils and two 6-series airfoils. Results regarding the factors affecting comparison of data from various test facilities, root-mean-square pressure pulsations, and root-mean-square force fluctuations are provided.
Date: July 26, 1956
Creator: Lindsey, Walter F. & Ladson, Charles L.
Item Type: Refine your search to only Report
open access

Pilot Plant Fluorination of Uranium Fuel Elements by Bromine Trifluoride

Description: The so-called Fluoride Volatility Processes refer to several proposed non-aqueous methods of processing irradiated fuel elements. In each of these methods, the uranium is fluorinated to uranium hexafluoride and then decontaminated by distillation. One of the methods, involving direct fluorination of the uranium by bromine trifluoride, has been under investigation at BNL since 1950; subsequently a pilot plant was built to study this step of the process. The objectives of the program were to inve… more
Date: July 26, 1956
Creator: Strickland, G.; Horn, F. L. & Johnson, R.
Item Type: Refine your search to only Report
open access

Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01

Description: Memorandum presenting an investigation at Mach numbers of 1.61 and 2.01 to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results regarding pressure distributions, spanwise loadings, and integrated coefficients are provided.
Date: July 26, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
open access

Pressure distributions and aerodynamic characteristics of several spoiler-type controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results of the tests indicated that the incremental pressure distributions due to spoiler were in agreement with previous results as long as the spoiler was not too close to a break in the wing surface or the wing tip.
Date: July 26, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
open access

Zero-Lift Drag of a Series of Bomb Shapes at Mach Numbers From 0.60 to 1.10

Description: Report presenting zero-lift drag data obtained on a series of six bomb shapes. Five configurations had the same body shape with different body-surface conditions and profile and plan form of fins, and the sixth had a different and longer body shape. Results regarding the effect of blunt trailing edge, blunt leading edge, fin thickness, and body surface are provided.
Date: July 26, 1956
Creator: Stoney, William E., Jr. & Royall, John F.
Item Type: Refine your search to only Report
open access

Neutron Leakage Through Iron

Description: Neutron attenuation in the old pile shields is dependent more and more on the slowing down characteristics of the iron as the hydrogen is baked out of the masonite. For neutrons above 1 or 2 Mev, iron does a good job by inelastic scattering. However, below this energy attenuation can be done only by the gradual moderation by elastic scattering to thermal energies with subsequent capture in the iron. Since iron is heavy and thus a poor moderator, there is a good possibility that many neutrons of… more
Date: July 25, 1956
Creator: Wood, D. E.
Item Type: Refine your search to only Report
open access

Use of Truncated Flapped Airfoils for Impingement and Icing Tests of Full-Scale Leading-Edge Sections

Description: From Summary: "In an effort to increase the operational range of existing small icing tunnels, the use of truncated airfoil sections has been suggested. With truncated airfoils, large-scale or even full-scale wing-icing-protection systems could be evaluated. Therefore, experimental studies were conducted in the NACA Lewis laboratory icing tunnel with an NACA 651-212 airfoil section to determine the effect of truncating the airfoil chord on velocity distribution and impingement characteristics. … more
Date: July 24, 1956
Creator: von Glahn, Uwe H.
Item Type: Refine your search to only Report
open access

Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-Body-Tail Configuration in Combination With Leading-Edge Devices

Description: Report presenting an investigation in the full-scale tunnel to determine the effects of the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. Results regarding half-span flaps and full-span flaps, pitching-moment and longitudinal trim characteristics, drag characteristics, lift-drag ratio, and lateral control are provided.
Date: July 20, 1956
Creator: McLemore, H. Clyde & Fink, Marvin P.
Item Type: Refine your search to only Report
open access

Effect of Wing Size and Amount of Indentation on Applicability of Transonic Area Rule to Swept-Wing Configurations

Description: Memorandum presenting a systematic transonic zero-lift drag investigation utilizing a swept-wing configuration with three different ratios of wing to fuselage size utilizing a 6-inch helium gun. The experiments and comparisons with other results indicated that the reduction of pressure drag obtainable from partial indentation is approximately proportional to the amount of indentation employed up to a Mach number of 1.3. Results regarding the basic data, total drag, pressure drag, equivalent bod… more
Date: July 20, 1956
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
open access

Flight-determined transonic lift and drag characteristics of the YF-102 airplane with two wing configurations

Description: Report presenting lift and drag characteristics of the Convair YF-102 airplane for symmetrical wing configuration and for the cambered wing configuration. Data were obtained for a variety of lift coefficients, altitudes, and Mach numbers. Results regarding lift, drag, and some flight-tunnel comparisons are provided.
Date: July 20, 1956
Creator: Saltzman, Edwin J.; Bellman, Donald R. & Musialowski, Norman T.
Item Type: Refine your search to only Report
open access

Free-Flight Investigation of Effects of Simulated Sonic Turbojet Exhaust on the Drag of Twin-Jet Boattail Bodies at Transonic Speeds

Description: Memorandum presenting a flight investigation to determine the effect of a propulsive jet on the zero-lift drag characteristics of two twin-exit boat-tailed bodies at transonic speeds. The two models had ratios of jet area to base area of 0.394 and 0.590 and covered a Mach number range of 0.8 to 1.15. A slight reduction in drag coefficients from power-off values are obtained during power-on flight for both models.
Date: July 20, 1956
Creator: Leiss, Abraham
Item Type: Refine your search to only Report
open access

Heat Transfer and Pressure Distribution at a Mach Number of 6.8 on Bodies With Conical Flares and Extensive Flow Separation

Description: Report presenting an investigation of heat transfer and pressure distribution on flared bodies under laminar, transitional, and turbulent boundary-layer conditions at Mach number 6.8. Information about flow characteristics, flare drag, and the relationship between flare drag and flare heating is provided.
Date: July 20, 1956
Creator: Becker, John V. & Korycinski, Peter F.
Item Type: Refine your search to only Report
open access

A Wind-Tunnel Investigation of the Effect of Nose Ring Spoilers on a Low-Speed Slowly Spinning Fin-Stabilized Rocket

Description: Memorandum presenting an investigation made in the stability tunnel with a model of a low-speed slowly spinning fin-stabilized rocket to determine the effectiveness of a nose ring spoiler in reducing the unstable Magnus moments on a sting-mounted completely spinning model and, if possible, to find the effect of a nonspinning center section, used in a previous investigation, on the unstable Magnus moment.
Date: July 20, 1956
Creator: Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
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