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Induction system characteristics and engine surge occurrence for two fighter-type airplanes

Description: Report presenting an investigation to measure and to compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbo-jet engines, but with dissimilar inlets. Results regarding compressor-face total-pressure surveys and surges encountered are provided.
Date: May 26, 1958
Creator: Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department

Examination of Factors Affecting the Quality of Vacuum Induction-Melted Uranium

Description: The following report examines primarily water and air factors that affect the quality of vacuum induction-melted uranium, yet follows experiments with other factors such as graphite and zirconium crucibles under dry and wet conditions, usage of hydrogen, oxygen, CO and other subject admitted to determine pressure-time relationships and residual gas compositions, as well as a study of water-gas reaction within the furnace.
Date: July 3, 1958
Creator: Endebrock, Roy W.; Foster, Ellis L. & Dickerson, Ronald F.
Partner: UNT Libraries Government Documents Department

Examination of Factors Affecting the Quality of Vacuum Induction-Melted Uranium

Description: The following report examines primarily water and air factors that affect the quality of vacuum induction-melted uranium, yet follows experiments with other factors such as graphite and zirconium crucibles under dry and wet conditions, usage of hydrogen, oxygen, CO and other subject admitted to determine pressure-time relationships and residual gas compositions, as well as a study of water-gas reaction within the furnace.
Date: July 3, 1958
Creator: Endebrock, Roy W.; Foster, Ellis L. & Dickerson, Ronald F.
Partner: UNT Libraries Government Documents Department

An experimental investigation at subsonic speeds of a scoop-type air-induction system for a supersonic airplane

Description: Report presenting an investigation at subsonic speeds of a scoop-type air-induction system designed for use at subsonic and supersonic speeds. Measurements of the ram-recovery ratio and static pressures in a scoop-type intake on the upper surface of the fuselage were taken for a large range of mass-flow ratios, angles of attack, and angles of sideslip.
Date: July 19, 1951
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

Approximate effect of leading-edge thickness, incidence angle, and inlet mach number on inlet losses for high-solidity cascades of low cambered blades

Description: Report presenting an approximate, theoretical analysis of the inlet or induction losses due to subsonic flow into a high-solidity cascade of finite thickness blades at incidence angle. Results indicated that the losses can become considerable for large deviations from the design incidence such as compressor off-design operating conditions. Results regarding the computational results, significance of assumptions and limitations, comparison of theoretical approximation with actual compressor results, and applicability of the results are provided.
Date: December 1954
Creator: Wright, Linwood C.
Partner: UNT Libraries Government Documents Department

An analytical study of the comparative performance of six air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 2.0

Description: Report presenting an extension of NACA RM A52C14 about inlet design and performance for Mach numbers of 1.5 to 2.0. A two-dimensional inviscid analysis is used to compare the performance of several types of inlets when used in conjunction with a turbojet engine with constant-volume air flow. Results regarding air delivery and air requirements, drag factors, evaluation of inlet performance, significance of the drag summation, and inlet and engine-matching considerations are provided.
Date: October 9, 1953
Creator: Watson, Earl C.
Partner: UNT Libraries Government Documents Department

Summary report on the induction of water to the inlet air as a means of internal cooling in aircraft-engine cylinders

Description: Report presenting investigations of a full-scale air-cooled aircraft-engine cylinder of 202-cubic-inch displacement to determine the effects of internal cooling by water induction on the maximum permissible power and output of an internal-combustion engine. Results regarding the maximum permissible engine performance, engine temperatures, and constant inlet-air pressure investigations are provided.
Date: August 15, 1942
Creator: Rothrock, Addison M. & Jones, Anthony W.
Partner: UNT Libraries Government Documents Department

Dependence of Magnetic Hysteresis upon Wave Form

Description: Report issued by the Bureau of Standards over studies on magnetic hysteresis and its dependence upon wave form. Methods and equipment used during the studies are presented and discussed. This report includes tables, and illustrations.
Date: 1909
Creator: Lloyd, Morton G.
Partner: UNT Libraries Government Documents Department

An investigation at transonic speeds of the aerodynamic characteristics of an air inlet installed in the root of a 45 degree sweptback wing

Description: Report presenting an investigation in the transonic blowdown tunnel from Mach numbers 0.80 to 1.41 to determine the increments in lift and drag due to installation of a triangular-shaped air inlet in the root of a 45 degree sweptback wing and to determine the internal flow characteristics of the inlet. Results regarding pressure measurements of the inlet model, force measurements of basic and inlet models, and effect of boundary-layer bypass scoop and fuselage nose configuration on characteristics of inlet model are presented.
Date: October 1, 1952
Creator: Howell, Robert R. & Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department

The induction of water to the inlet air as a means of internal cooling in aircraft-engine cylinders

Description: Report presents the results of investigations conducted on a full-scale air-cooled aircraft-engine cylinder of 202-cubic inch displacement to determine the effects of internal cooling by water induction on the maximum permissible power and output of an internal-combustion engine. For a range of fuel-air and water-fuel ratios, the engine inlet pressure was increased until knock was detected aurally, the power was then decreased 7 percent holding the ratios constant. The data indicated that water was a very effective internal coolant, permitting large increases in engine power as limited by either knock or by cylinder temperatures.
Date: 1943
Creator: Rothrock, Addison M.; Krsek, Alois, Jr. & Jones, Anthony W.
Partner: UNT Libraries Government Documents Department

An Analytical Study of the Comparative Performance of Four Air-Induction Systems for Turbojet-Powered Airplanes Designed to Operate at Mach Numbers Up to 1.5

Description: Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.
Date: June 17, 1952
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department

Effect of Modifications to Induction System on Altitude Performance of V-1710-93 Engine 3: Use of Parabolic Rotating Guide Vanes and NACA Designed Auxiliary-Stage Inlet Elbow and Interstage Duct

Description: "Bench runs of a modified V-1710-93 engine equipped with a two-stage supercharger, interstage carburetor, aftercooler assembly, and backfire screens have been made at a simulated altitude of 29,000 feet to determine the effect of several induction-system modifications on the engine and supercharger performance. The standard guide vanes on the auxiliary- and engine-stage superchargers were replaced by rotating guide vanes with a parabolic blade profile. The auxiliary-stage inlet elbow and interstage duct were replaced with new units of NACA design. These modifications were made one at a time and data were obtained after each change to determine the effect of each modification" (p. 1).
Date: January 16, 1947
Creator: Standahar, Ray M. & McCarty, James S.
Partner: UNT Libraries Government Documents Department

Induction Furnace Testing of the Durability of Prototype Crucibles in a Molten Metal Environment

Description: Engineered ceramic crucibles are commonly used to contain molten metal. Besides high temperature stability, other desired crucible characteristics include thermal shock resistance, minimal reaction with the molten metal and resistance to attack from the base metal oxide formed during melting. When used in an induction furnace, they can be employed as a “semi-permanent” crucible incorporating a dry ram backup and a ceramic cap. This report covers several 250-lb single melt crucible tests in an air melt induction furnace. These tests consisted of melting a charge of 17-4PH stainless steel, holding the charge molten for two hours before pouring off the heat and then subsequently sectioning the crucible to review the extent of erosion, penetration and other physical characteristics. Selected temperature readings were made throughout each melt. Chemistry samples were also taken from each heat periodically throughout the hold. The manganese level was observed to affect the rate of chromium loss in a non-linear fashion.
Date: 2005-09~
Creator: Jablonski, Paul D.
Partner: UNT Libraries Government Documents Department

Cosmological AMR MHD with Enzo

Description: In this work, we present EnzoMHD, the extension of the cosmological code Enzoto include magnetic fields. We use the hyperbolic solver of Li et al. (2008) for the computation of interface fluxes. We use constrained transport methods of Balsara & Spicer (1999) and Gardiner & Stone (2005) to advance the induction equation, the reconstruction technique of Balsara (2001) to extend the Adaptive Mesh Refinement of Berger & Colella (1989) already used in Enzo, though formulated in a slightly different way for ease of implementation. This combination of methods preserves the divergence of the magnetic field to machine precision. We use operator splitting to include gravity and cosmological expansion. We then present a series of cosmological and non cosmologjcal tests problems to demonstrate the quality of solution resulting from this combination of solvers.
Date: January 1, 2009
Creator: Xu, Hao; Li, Hui & Li, Shengtai
Partner: UNT Libraries Government Documents Department

Longitudinal Resistive Stability of an Intense Charge Bunch in a Linear Accelerator

Description: A simple, but realistic, model is used to theoretically investigate the longitudinal stability of a non-relativistic bunch in the limit of small wall resistivity compared to self-reactance. It is shown that to lowest order--and in contrast with an infinitely long beam--that an intense bunch is stable against longitudinal collective modes. It is concluded that an induction linac remains a viable option as a driver for heavy ion inertial fusion.
Date: July 1, 1980
Creator: Channell, P.J.; Wurtele, J.S. & Sessler, A.M.
Partner: UNT Libraries Government Documents Department

The effect of entrance Mach number and lip shape on the subsonic characteristics of a scoop-type-air-induction system for a supersonic airplane

Description: Report presenting an investigation at subsonic speeds to determine the effects of lip shape and entrance Mach number on the characteristics of a scoop-type air-induction system designed for an airplane flying at supersonic speeds. Results regarding the ram-recovery ratio, static-pressure distribution, and drag are provided.
Date: January 9, 1952
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

Stacked insulator induction accelerator gaps

Description: Stacked insulators, with alternating layers of insulating material and conducting film, have been shown to support high surface electrical field stresses. We have investigated the application of the stacked insulator technology to the design of induction accelerator modules for the Relativistic-Klystron Two-Beam Accelerator program. The rf properties of the accelerating gaps using stacked insulators, particularly the impedance at frequencies above the beam pipe cutoff frequency, are investigated. Low impedance is critical for Relativistic-Klystron Two-Beam Accelerator applications where a high current, bunched beam is trsnsported through many accelerating gaps. An induction accelerator module designs using a stacked insulator is presented.
Date: May 1997
Creator: Houck, T. I.; Westenskow, G. A.; Kim, J. S.; Eylon, S.; Henestroza, E.; Yu, S. S. et al.
Partner: UNT Libraries Government Documents Department

Induction core performance

Description: Large masses of magnetic core material are required for many of the induction accelerator-based projects currently under study; the quantities required exceed 10<sup>7</sup> kg for a linear heavy-ion fusion driver, so core performance and cost are critical issues. We have evaluated cores of amorphous alloys from AlliedSignal and MRTI (Moscow Radio Technical Institute) and nanocrystalline alloys from Hitachi and Vacuumschmelze. The cores were of moderate size, between 1 and 11 kg. We characterized the materials in terms of the flux swing {Delta}B from -B<sub>remanent</sub> to +B<sub>saturation</sub>, and the energy loss versus dB/dt. We found sources for each material that could coat, wind, and then anneal the cores. This required the development of thin coatings that withstand 350-550° C anneal temperatures. The result is core performance near the ultimate small sample performance of each material, with higher {Delta}B and lower losses than the earlier approaches of using as-cast material or rewinding after anneal, in both, cases usually cowinding with thin mylar (-4µm thick). We are beginning system code studies of tradeoffs between {Delta}B and losses.
Date: August 14, 1998
Creator: Faltens, A; Meier, W R; Molvik, A W; Reginato, L & Smith, C
Partner: UNT Libraries Government Documents Department

Reaction field induced interatomic forces between atoms in the presense of a strong magnetic field

Description: It is shown that the reaction field induced in an atom by a strong magnetic field is of order B{alpha}² in atomic units (for magnetic field strength B and fine structure constant {alpha}). The reaction field causes a dipole-dipole interatomic potential energy to exist between a pair of atoms of order B<sup>3/2</sup>{alpha}<sup>7/2</sup>, such that B must be of order {alpha}<sup>-7/3</sup> for the interatomic energy to be of order one atomic unit. B of this order corresponds to a field strength of 1.66 x 10<sup>12</sup> G, which is within the regime of field strengths considered in recent studies of atoms and molecules in the presence of a strong magnetic field.
Date: March 23, 1999
Creator: Ritchie, A B
Partner: UNT Libraries Government Documents Department

Icing Tests of Aircraft-Engine Induction Systems

Description: Report presenting a program of icing tests conducted on an aircraft-engine induction system consisting of a Wright R-1820, G-200 blower section, Holley 1375-F carburetor and adapter, and specially built air scoop. The primary purpose of the investigation was to determine the effect of a number of possible factors on icing of engine-induction systems, including carburetor-air temperature, air-moisture content, water-droplet size, throttle opening, mixture ratio, rate of air flow, altitude, and others.
Date: January 1943
Creator: Kimball, Leo B.
Partner: UNT Libraries Government Documents Department