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Effect of moderate air flow on the distribution of fuel sprays after injection cut-off

Description: "High-speed motion pictures were taken of fuel sprays with the NACA spray-photographic apparatus to study the distribution of the liquid fuel from the instant of injection cut-off until about 0.05 second later. The fuel was injected into a glass-walled chamber in which the air density was varied from 1 to 13 times atmospheric air density (0.0765 to 0.99 pound per cubic foot) and in which the air was at room temperature. The air in the chamber was set in motion by means of a fan, and was directe… more
Date: February 14, 1934
Creator: Rothrock, A. M. & Spencer, R. C.
Partner: UNT Libraries Government Documents Department
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Comparison of observed and calculated flattening at 105-D

Description: The total power output of a unit may be represented by the power output of the most productive tube or tubes multiplied by a quantity designated as the ``number of effective tubes.`` The number of effective tubes observed at 105-D under two different arrangements of poisoned columns has been compared with values of this quantity calculated from theory. It was found that in each case the observed number of effective tubes was about 5% less than the ideal number obtainable by an optimum arrangeme… more
Date: February 14, 1945
Creator: Gast, P. F.
Partner: UNT Libraries Government Documents Department
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Pile Heat Exchanger Calculations

Description: Abstract. Some idealized calculations (CP-807) relating to the design of heat exchangers for minimum holdup of pile liquid are presented in compact form to facilitate quick estimates. Their use is illustrated by application to a falling film type exchanger.
Date: February 14, 1945
Creator: Young, Gale Jay
Partner: UNT Libraries Government Documents Department
open access

Effect of Routing Upon Temperature of Cooling Stream

Description: With discussion under way concerning power production by chain reacting piles, it becomes pertinent to consider the ration of the temperature of the hottest spot in the pile to the average exit temperature of the cooling stream. This is important because the temperature of the hottest spot in the pile is one of the limiting factors in determining the maximum power at which a pile can be operated. However, the higher the temperature of the emerging cooling stream, the more efficient can be the t… more
Date: February 14, 1946
Creator: Cahn, Albert S., Jr.
Partner: UNT Libraries Government Documents Department
open access

Summary of lateral-control research

Description: "A summary has been made of the available information on lateral control. A discussion is given of the criterions used in lateral-control specifications, of the factors involved in obtaining satisfactory lateral control, and of the methods employed in making lateral-control investigations in flight and in wind tunnels. The available data on conventional flap-type ailerons having various types of aerodynamic balance are presented in a form convenient for use in design. The characteristics of spo… more
Date: February 14, 1946
Creator: Toll, Thomas A.
Partner: UNT Libraries Government Documents Department
open access

Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Description: Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps i… more
Date: February 14, 1947
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of a Model of the Lockheed YP-80A Airplane Including Correlation with Flight Tests and Tests of Dive-Recovery Flaps

Description: "This report contains the results of tests of a 1/3-scale model of the Lockheed YP-90A "Shooting Star" airplane and a comparison of drag, maximum lift coefficient, and elevator angle required for level flight as measured in the wind tunnel and in flight. Included in the report are the general aerodynamic characteristics of the model and of two types of dive-recovery flaps, one at several positions along the chord on the lower surface of the wing and the other on the lower surface of the fuselag… more
Date: February 14, 1947
Creator: Cleary, Joseph W. & Gray, Lyle J.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effects of Sweep on the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel

Description: "An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper ration of 2.5:1.0, has been tested with no sweep, and 30 deg and 45 deg of sweepback and sweepforward in conjunction with a typical fuselage at Mach numbers from 0.60 to 0.96 at angles of attack generally between -2 deg and 10 deg in the Langley 8-foot high-speed tunnel. Sweep was obtained by rotating the wing semispans about a point in the plane of symmetry. The normal-force, pitching-moment, … more
Date: February 14, 1947
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a thin straight wing of aspect ratio 4 by the NACA wing-flow method: Lift and pitching-moment characteristics of the wing alone

Description: This report presents measurements of the lift and pitching-moment characteristics of a straight wing of aspect ratio 4, taper ratio 0.5, having a symmetrical double-wedge airfoil section with a maximum thickness of 4.4-percent chord. The tests were conducted in the Mach number range 0.51 to 1.20, Reynolds numbers 380,000 to 660,000, by the NACA wing-flow method. The results are compared with theory and with wind-tunnel tests of a similar model. It is indicated that in the Mach number range 0.82… more
Date: February 14, 1949
Creator: Rathert, George A., Jr.; Hanson, Carl M. & Rolls, L. Stewart
Partner: UNT Libraries Government Documents Department
open access

LITERATURE SEARCH ON LEAD-BISMUTH ALLOYS

Description: BS>The use of a lead-bismuth alloy as a coolant in the removal of heat from power-generating nuclear reactors was considered with the possibility that its ternary alloy with uranium or plutonium might be of use in a reactor of the circulating-liquid-fuel type. Information collected from the literature covering phase-equilibrium studies, physicalproperty data, and reactivity of this alloy toward other substances is presented. (auth)
Date: February 14, 1950
Creator: Lee, M.E.
Partner: UNT Libraries Government Documents Department
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Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees

Description: Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.
Date: February 14, 1950
Creator: Turner, Thomas R.
Partner: UNT Libraries Government Documents Department
open access

Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions

Description: A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.
Date: February 14, 1950
Creator: Gray, W. H. & Hunt, Robert M.
Partner: UNT Libraries Government Documents Department
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Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip

Description: Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
Date: February 14, 1951
Creator: Weinstein, Maynard I. & Davids, Joseph
Partner: UNT Libraries Government Documents Department
open access

Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel

Description: "At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Sim… more
Date: February 14, 1951
Creator: Vasu, George; Schwent, Glennon V. & Ketchum, James R.
Partner: UNT Libraries Government Documents Department
open access

Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18

Description: Memorandum presenting a study using a suspended flat plate to continuously vary the Mach number in the 18- by 18-inch Mach number 1.91 supersonic tunnel. The technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced. Results regarding the plate calibration and inlet performance are provided.
Date: February 14, 1951
Creator: Fox, Jerome L.
Partner: UNT Libraries Government Documents Department
open access

V. Multiplying Lattices of the Hollow Type

Description: A two-group approximation of the fission ratios and Pu production in an infinite hollow matrix is developed
Date: February 14, 1951
Creator: Brown, Harold
Partner: UNT Libraries Government Documents Department
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Analysis of coolant-flow requirements for an improved, internal-strut-supported, air-cooled turbine-rotor blade

Description: From Introduction: "The purpose of this report is to present the results of the investigation, to compare the coolant-flow requirements of the two configurations, and to show what advantages an air-cooled internal-strut-supported blade may have over an equivalent shell-supported air-cooled blade."
Date: February 14, 1952
Creator: Schramm, Wilson B. & Nachtigall, Alfred J.
Partner: UNT Libraries Government Documents Department
open access

Chemistry Division Quarterly Progress Report for Period Ending June 30, 1951

Description: Quarterly technical report including reports on chemistry of source, fissionable, and structural elements, nuclear chemistry, radio-organic chemistry, chemistry of separations processes, chemical physics, radiation chemistry, and instrumentation of the Chemistry Division of the Oak Ridge National Laboratory (ORNL). [From Abstract]
Date: February 14, 1952
Creator: Lind, S. C.; Boyd, G. E. & Bredig, M. A.
Partner: UNT Libraries Government Documents Department
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Combustion efficiency performance of a MIL-F-5624 type fuel and monomethylnapthalene in a single vaporizing combustor

Description: Report presenting an investigation conducted with a conventional turbojet fuel, MIL-F-5624 (JP-3), and a low-volatility, high-density hydrocarbon, monomethylnaphthalene, in a vaporizing-type combustor to determine the combustion efficiency for variations in inlet-air conditions and fuel flow and to what extent fuel vaporization would minimize differences in combustion efficiency between the two fuels. Results regarding the performance of the combustor, correlation parameter, pressure-drop chara… more
Date: February 14, 1952
Creator: Jones, Anthony W. & Cook, William P.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of the Effect of Forebody Bluntness on the Pressure Recovery and Drag of a Twin-Scoop Inlet-Body Combination at Mach Numbers of 1.4 and 1.7

Description: Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop inlet-body combination measured at Mach numbers 1.4 and 1.7 at zero angle of attack. Tests were made of the inlet-body combination with an ogival forebody, an ogival forebody with a small amount of bluntness near the tip, and two forebodies of elliptical longitudinal section. Results regarding the effect of forebody bluntness on pressure recovery, effect of forebody bluntness on mass-flow ratio, and the effects of … more
Date: February 14, 1952
Creator: Stroud, John F.
Partner: UNT Libraries Government Documents Department
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Pressure Distribution and Aerodynamic Coefficients Associated With Heat Addition to Supersonic Air Stream Adjacent to Two-Dimensional Supersonic Wing

Description: "The modifications in the pressure distributions and the aerodynamic coefficients associated with additions of heat to the two-dimensional supersonic in viscid flow field adjacent to the lower surface of of a 5-percent-thickness symmetrical circular-arc wing are presented in this report. The pressure distributions are obtained by the use of graphical method which gives the two-dimensional supersonic inviscid flow field obtained with moderate heat addition. The variation is given of the lift-dra… more
Date: February 14, 1952
Creator: Pinkel, I. Irving; Serafini, John S. & Gregg, John L.
Partner: UNT Libraries Government Documents Department
open access

Examination of Irradiated Uranium-Chromium Alloy Slugs

Description: Production Test 313-105-13-M authorized the irradiation of a uranium - 0.4 atomic per cent chromium alloy to determine the relative stability of this material during irradiation. Five tubes, each containing six four-inch alloy slugs, were irradiated to exposures ranging from 156 to 834 MWD/T. This report describes the results of the visual examination of the bare uranium alloy slugs and the results of the test to determine slug breaking strength. The breaking strength of both the U-Cr alloy slu… more
Date: February 14, 1955
Creator: Kratzer, W. K.
Partner: UNT Libraries Government Documents Department
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