UNT Libraries Government Documents Department - 27 Matching Results

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Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Description: Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.
Date: July 26, 1955
Creator: Welna, Harry J. & Reilly, Dwight H.
Item Type: Refine your search to only Report
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Investigation of Aerodynamic and Icing Characteristics of Water-Inertia-Separation Inlets for Turbojet Engines

Description: "The results of an investigation of several internal water-inertia-separation inlets consisting of a main duct and an alternate duct designed to prevent automatically the entrance of large quantities of water into a turbojet engine in icing conditions are presented. Total-pressure losses and icing characteristics for a direct-ram inlet and the inertia-separation inlets are compared at similar aerodynamic and simulated icing conditions. Complete ice protection for inlet guide vanes could not be … more
Date: July 26, 1950
Creator: von Glahn, Uwe & Blatz, Robert E.
Item Type: Refine your search to only Report
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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

The effects of compressibility on the pressures on a body of revolution and on the aerodynamic characteristics of a wing-nacelle combination consisting of the body of revolution mounted on a swept-back wing

Description: Memorandum presenting an investigation of the effects of compressibility on the forces, pitching moments, and surface pressures on a wing-nacelle combination. The leading edge of the wing was swept back 37.25 degrees and the nacelle was a body of revolution with a fineness ratio of 6.5. The effects of compressibility on the surface pressures and on the drag of a body of revolution similar to the nacelle were also determined.
Date: July 26, 1950
Creator: Boltz, Frederick W. & Beam, Benjamin H.
Item Type: Refine your search to only Report
open access

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

Foreign-object retention and flow characteristics of retractable engine-inlet screens

Description: Report presenting an investigation to determine and improve on the foreign-object-retention capabilities and pressure-loss characteristics of rectractable engine-inlet screens. Testing occurred with two commerically made retractable screens installed in the engine-inlet sections for which they were designed. Results regarding the retention for both the original and modified screens and pressure tests are provided.
Date: July 26, 1957
Creator: Steffen, Fred W. & Rodert, Lewis A.
Item Type: Refine your search to only Report
open access

Propellant vaporization as a criterion for rocket-engine design : experimental effect of fuel temperature on liquid-oxygen - heptane performance

Description: Characteristic exhaust velocity of a 200-pound-thrust rocket engine was evaluated for fuel temperatures of -90 degrees, and 200 degrees f with a spray formed by two impinging heptane jets reacting in a highly atomized oxygen atmosphere. Tests covered a range of mixture ratios and chamber lengths. The characteristic exhaust-velocity efficiency increased 2 percent for a 290 degree f increase in fuel temperature. This increase in performance can be compared with that obtained by increasing chamber… more
Date: July 26, 1957
Creator: Heidmann, M. F.
Item Type: Refine your search to only Report
open access

Arrangements of jet engine and airframe for increased range

Description: Report presenting an evaluation of a number of factors affecting engine-airframe arrangements in terms of range. Appropriate equations are developed and evaluated for a range of Mach numbers, ramjet and turbojet engines at several cycle temperatures, and two airplane lift-drag ratios. Some of the factors explored include inlet locations, jet cant for lift, engine moments for trim, a combination of the three factors, and the use of boundary layer in the engine.
Date: July 26, 1957
Creator: Luidens, Roger W.
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

Pilot Plant Fluorination of Uranium Fuel Elements by Bromine Trifluoride

Description: Report issued by the Brookhaven National Laboratory discussing methods of processing reactor fuels such as uranium. As stated in the objective, "the primary objective of the project was to determine the effect of temperature, solution composition, and flow rate on the dissolving time for natural uranium slugs of varying history" (p. 2). This report includes tables, illustrations, and photographs.
Date: July 26, 1957
Creator: Strickland, G.; Horn, F. L. & Johnson, R.
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. Report 412FF124

Description: BS>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 emis… more
Date: July 26, 1956
Creator: Helstrom, C.W.
Item Type: Refine your search to only Report
open access

QUANTIZATION OF CRYSTAL VIBRATIONS

Description: Although the Born-von Karman treatment of the dynamics of crystal lattices is superior to that of Debye, the conABSTRACTS tinuum model of Debye is more amenable to computation; therefore the Debye treatment is used to obtain frequencies at a maximum energy. From the classic Hamiltonian of the solid, quantization is carried out by the Schroedinger method. The thermodymamic functions are obtained, and the mean square displacement is derived. (J.S.R.)
Date: July 26, 1957
Creator: DeMarcus, W. C.
Item Type: Refine your search to only Report
open access

Plastic Flow During Extrusion of Tubing

Description: Abstract: "A study of plastic flow during the extrusion of tubing was made by extruding colored Plasticine billets in a small-scale extrusion press. Decreasing the included angle of the conical die and tapering the ram end of the billet decreased the amount of coextrusion of the backer block into the tubing, lubricating the billet also decreased coextrusion."
Date: July 26, 1955
Creator: Saller, Henry A.; Keeler, John R. & Cuddy, Lee J.
Item Type: Refine your search to only Report
open access

Dissolution of Aluminum-Canned Thorium

Description: The following report studies the dissolution of aluminum-canned thorium, providing results that suggest a dissolution cycle that permits the separation of the canned-slug components.
Date: July 26, 1955
Creator: Beach, John G.; Schickner, William C. & Faust, Charles L.
Item Type: Refine your search to only Report
open access

Hanford Atomic Products Operation monthly report, June 1954

Description: This document presents a summary of work and progress at the Hanford Engineer Works for June 1954. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summaries work for the Technical, Design, and Project Sections. … more
Date: July 26, 1954
Item Type: Refine your search to only Report
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