Search Results

open access

Three-dimensional Numerical Investigation of Electron Transport with Rotating Spoke in a Cylindrical Anode Layer Hall Plasma Accelerator

Description: The oscillation behavior described in [Tang et. al, Phys. Plasmas 19, 073519 (2012)] di ers too greatly from previous experimental and numerical studies to claim observation of the same phenomenon. Most signi cantly, the rotation velocity in [Tang et. al, Phys. Plasmas 19, 073519 (2012)] is three orders of magnitude larger than that of typical \rotating spoke" phenomena. Several physical and numerical considerations are presented to more accurately understand the numerical results of [Tang… more
Date: August 27, 1012
Creator: Ellison, C. Leland; Matyash, K.; Parker, J. B.; Raitses, Y. & Fisch, N. J.
Partner: UNT Libraries Government Documents Department
open access

Effect of Tip Shape and Dihedral on Lateral-Stability Characteristics

Description: This report presents the results of wind tunnel tests to determine the effect of wing-tip shape and dihedral on some of the aerodynamic characteristics of Clark Y wings that affect the performance and lateral stability of airplanes. Force tests at several angles of yaw and rotation tests at zero yaw were made. From these tests the rates of change of rolling moment, yawing moment, and cross-wind force coefficients with angle of yaw and the rate of change of rolling moment coefficient with rollin… more
Date: August 27, 1935
Creator: Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department
open access

Project 9536, metal turnings - fire hazard

Description: The turnings have proved to be highly inflammable and subject to spontaneous ignition. Several experiments have been conducted at Herring-Hall-Marvin Safe Company, Hamilton, Ohio, and Baker Brothers, Inc., Toledo, Ohio, and in addition there have been a number of accidental fires, of which at least three were spontaneous. Fires of quantities ranging from several pounds to several hundred pounds have been experienced and a number of extinguishers have been tried. Records of this work are availab… more
Date: August 27, 1943
Partner: UNT Libraries Government Documents Department
open access

Reduction of Fuel-Vapor Loss by Omitting Some of the Fuel Constituents Normally Lost During Flight

Description: Report discussing an investigation to determine the effect of omitting some of the fuel constituents in AN-F-28 Amendment 2 fuel that are normally lost in flight on fuel-vapor loss. Removing the components was found to decrease the fuel-vapor loss and increase the critical altitudes.
Date: August 27, 1945
Creator: Stone, Charles S. & Kramer, Walter E.
Partner: UNT Libraries Government Documents Department
open access

Fractionation of Fission Products and Heavy Elements by Volatilization Methods

Description: Technical report describing the attempt to separate the long lived fission product oxides by volatilization methods. A fractionization crucible was used. The fractionations give a fair idea of the relative volatilities of the longer lived fission products and also of the degrees of separation of the plutonium oxide or oxides from the fission products.
Date: August 27, 1946
Creator: Erway, N. D. & Simpson, O. C.
Partner: UNT Libraries Government Documents Department
open access

GASEOUS FLOW

Description: No Description Available.
Date: August 27, 1946
Creator: Normand, C. E.
Partner: UNT Libraries Government Documents Department
open access

Neutron Diffusion in a Space Lattice of Fissionable and Absorbing Materials

Description: Methods are developed for estimating the effect on a critical assembly of fabricating it as a lattice rather than in the more simply interpreted homogeneous manner. An idealized case is discussed supposing an infinite medium in which fission, elastic scattering and absorption can occur, neutrons of only one velocity present, and the neutron m.f.p. independent of position and equal to unity with the unit of length use. (auth)
Date: August 27, 1946
Creator: Welton, T. A. & Feynman, R. P.
Partner: UNT Libraries Government Documents Department
open access

Calculated Condenser Performance for a Mercury-Turbine Power Plant for Aircraft

Description: "As part of an investigation of the application of nuclear energy to various types of power plants for aircraft, calculations have been made to determine the effect of several operating conditions on the performance of condensers for mercury-turbine power plants. The analysis covered 8 range of turbine-outlet pressures from 1 to 200 pounds per square inch absolute, turbine-inlet pressures from 300 to 700 pounds per square inch absolute,and a range of condenser cooling-air pressure drops, airpla… more
Date: August 27, 1948
Creator: Doyle, Ronald B.
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Flight Measurements With Calculations of the Loss in Rolling Effectiveness Due to Wing Twist

Description: "A flight investigation was conducted with a fighter-type airplane to determine the loss in rolling effectiveness due to wing twist, and the results are compared with the loss in rolling effectiveness calculated by use of a simplified method. The computed rolling velocities showed good agreement with experimentally determined rolling velocities throughout the Mach number range covered by the flights. Extrapolation of the flight data indicated a Mach number for reversal which agreed well with th… more
Date: August 27, 1948
Creator: Cooney, T. V. & Wollner, Bertram C.
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Rolling Effectiveness of Several Delta Wing - Aileron Configurations at Transonic and Supersonic Speeds

Description: Report presenting testing of several delta wing-aileron configurations as part of a general investigation of their rolling effectiveness characteristics at transonic and supersonic speeds. Results regarding wing-aileron rolling effectiveness and drag are provided.
Date: August 27, 1948
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 1 The Effect of Combination With a Body Revolution and Height Above a Ground Plane

Description: Memorandum presenting low-speed wind-tunnel test conducted of a triangular wing of aspect ratio 2.0 with a symmetrical double-wedge section with a maximum thickness of 5 percent of the chord at 20 percent of the chord. The wing was also tested in the presence of a ground plane. Results regarding isolated wing and wing-body combinations, split-flap effectiveness, and ground effect are provided.
Date: August 27, 1948
Creator: Rose, Leonard M.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method

Description: "An investigation of two semispan wings swept back 50 degrees 38 minutes was conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.68 to 1.15 by use of the transonic-bump technique. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one was an untwisted uncambered wing and the other was the same wing but incorporated twist and camber designed to give uniform load at a lift coefficient of 0.25 at … more
Date: August 27, 1951
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Longitudinal Characteristics of the X-3 Configuration With Wing and Horizontal Tail Surfaces of Aspect Ratio 3.0 by Means of Rocket-Propelled Models: Results at High Lift Coefficients

Description: "A rocket-propelled model of the X-3 configuration equipped with an all-movable tail of aspect ratio 3.0 has been flown to determine the longitudinal characteristics of this configuration at high lift coefficients. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on lift, drag, longitudinal stability, and longitudinal trim change. The primary result of the tests was that the configuration was indicated to have very unstable tendencies at lift… more
Date: August 27, 1951
Creator: Peck, Robert F. & Mitchell, Jesse L.
Partner: UNT Libraries Government Documents Department
open access

Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specificatio… more
Date: August 27, 1952
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Partner: UNT Libraries Government Documents Department
open access

The Calculation of Certain Static Aeroelastic Phenomena of Wings With Tip Tanks or Boom-Mounted Lifting Surfaces

Description: Report presenting the use of the matrix-integration method for calculating static aeroelastic phenomena on a wing with concentrated aerodynamic forces at the tip due to tip tanks or boom-mounted lifting surfaces. The results indicate that the presence of a tip tank on an unswept wing tends to deteriorate its static aeroelastic characteristics and that a lift surface geared to the aileron and mounted on a boom ahead of the tip may improve the static aeroelastic characteristics to warrant conside… more
Date: August 27, 1952
Creator: Diederich, Franklin W. & Foss, Kenneth A.
Partner: UNT Libraries Government Documents Department
open access

A High Vacuum High Speed Ion Pump

Description: A vacuum pump based on the properties of a magnetically collimated electric discharge is described. It has a speed in the range 3000 to 7000 liters a second and a base pressure in the order of 10{sup-6}mm.
Date: August 27, 1952
Creator: Foster, J. S., Jr.; Lawrence, E. O. & Lofgren, E. J.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Low-Speed Static and Rotary Stability Derivatives of a 0.13-Scale Model of the Douglas D-558-II Airplane in the Landing Configuration

Description: Report presenting a wind-tunnel investigation to determine the low-speed static and rotary stability derivatives of a model of the Douglas D-558-II airplane in the landing configuration. Results regarding the static longitudinal characteristics, static lateral characteristics, characteristics in rolling flow, and characteristics in yawing flow are provided.
Date: August 27, 1952
Creator: Queijo, M. J. & Wells, Evalyn G.
Partner: UNT Libraries Government Documents Department
open access

An Improved Continuous Ether Extractor for the Determination of Uranium in Dissolver Solutions

Description: An improved continuous ether extractor is described. The modifications include a means of safely disposing of the active raffinate and a means of positivity checking the raffinate for completeness of uranium extraction. The results obtained on synthetic samples and on dissolver solutions are given. This work was undertaken because of a need for the determination of uranium in dissolver solutions with an accuracy of 0.1 per cent. After a review of available methods it was decided that a gravimet… more
Date: August 27, 1953
Creator: Bane, R. W. & Jensen, K. J.
Partner: UNT Libraries Government Documents Department
open access

Method for estimating combustion efficiency at altitude flight conditions from combustor tests at low pressures

Description: Report presenting the development and use of a chart for use in estimating the combustion efficiency of a turbojet at altitude flight conditions. The combustion efficiency chart is based on the assumption that the corrected gas flows, pressures, and temperatures of engine components other than the combustor are unique functions of corrected engine speed.
Date: August 27, 1953
Creator: Olson, Walter T.; Childs, J. Howard & Scull, Wilfred E.
Partner: UNT Libraries Government Documents Department
open access

Some Information on the Strength of Thick-Skin Wings With Multiweb and Multipost Stabilization

Description: Report presenting the results of strength tests on thick-skin wing structures. Some of the factors that were found to have influence on the buckling behavior and strength are shown with data and the conditions under which a combination of multiweb and multipost construction may be used are discussed. Results regarding circular-arc airfoils, multiweb beams, and multipost stiffened beams are provided.
Date: August 27, 1953
Creator: Anderson, Roger A.; Pride, Richard A. & Johnson, Aldie E., Jr.
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Measurement of the Aerodynamic Load on the Extended Slat of the Douglas D-558-II Research Airplane

Description: Report presenting a flight investigation of the aerodynamic loads of a partial-span extended leading-edge slat on the 35-degree sweptback wing of the Douglas D-558-II research airplane. The slat normal-force coefficient was found to increase with airplane normal-force coefficient until peak slat normal-force-coefficient was reached at approximately 2.2 to 2.4.
Date: August 27, 1953
Creator: Peele, James R.
Partner: UNT Libraries Government Documents Department
open access

Altitude investigation of 20-inch-diameter ram-jet engine with annular-piloted combustor

Description: From Introduction: "The combustor efficiency, combustor-inlet Mach number, and combustor total-pressure ratio of the annular-piloted combustor are presented herein. The effect of combustor-exit total pressure on combustor efficiency, and a comparison of configurations on the basis of specific fuel consumption are also presented."
Date: August 27, 1954
Creator: Henzel, James G. & Trout, Arthur M.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen