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Measurement of Large, High-Frequency, Short-Pulse Currents Using a Radial Shunt

Description: Abstract: "The measurement of large, high-frequency, short-pulse currents--ordinarily complicated by inductance, stray magnetic fields, and magnetic forces that tend to disassemble the measuring device--is simplified and made with an average error of 2-1/2% by the use of a specially developed noninductive radial shunt in conjuntion with an oscilloscope. The skin-effect correction is derived theoretically and the accuracy of the method is demonstrated."
Date: May 22, 1956
Creator: McFarlane, H. Bruce
Partner: UNT Libraries Government Documents Department
open access

Effect of Inlet-Guide-Vane Angle on Blade Vibration and Rotating Stall of 13-Stage Axial-Flow Compressor in Turbojet Engine

Description: Report presenting a blade-vibration and rotating-stall survey on a modified version of a production turbojet engine with a 13-stage axial-flow compressor with a design pressure ratio of 7 and an air flow of 120 pounds per second. This testing was carried out due to the problems rotating stall can cause with both experimental and production axial-flow compressors. Results regarding the rotating-stall patterns, rotor-blade vibrations, radial and axial strength of rotating stall, and maximum rotat… more
Date: May 22, 1956
Creator: Calvert, Howard F.; Medeiros, Arthur A. & Johnson, Donald F.
Partner: UNT Libraries Government Documents Department
open access

A Simplified Method for Approximating the Transient Motion in Angles of Attack and Sideslip During a Constant Rolling Maneuver

Description: "The transient motion in angles of attack and sideslip during a constant rolling maneuver has been analyzed. Simplified expressions are presented for the determination of the pertinent modes of motion as well as the modal coefficient corresponding to each mode. Calculations made with and without the derivatives for side force due to sideslip and lift-curve slope indicate that although these derivatives increase the total damping of the system they do not markedly affect the transient motion" (p… more
Date: May 22, 1956
Creator: Sternfield, Leonard
Partner: UNT Libraries Government Documents Department
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The change with mass-flow ratio of the cowl pressure drag of normal-shock inlets at supersonic speeds

Description: Report presenting pressure-drag coefficients and the changes in these coefficients with mass-flow ratio, which have been measured in tests of six open-nose conical cowls at an angle of attack of 0 degrees. Testing occurred in the Ames 8 by 8-inch supersonic wind tunnel at a range of Mach numbers. Results regarding pressure distributions, change in cowl pressure drag with mass-flow ratio, cowl pressure drag at a given mass-flow ratio, and changes in cowl pressure drag with mass-flow ratio as a f… more
Date: June 22, 1956
Creator: Davis, Wallace F. & Gowen, Forrest E.
Partner: UNT Libraries Government Documents Department
open access

Free-flight measurements of the zero-lift drag of several wings at Mach numbers from 1.4 to 3.8

Description: Report presenting the zero-lift drag of several wings obtained at supersonic Mach numbers in free flight with rocket-propelled models. The wings tested all had the same exposed area, mounted on the same basic body configuration, and had one of four different types of wings.
Date: June 22, 1956
Creator: Jackson, H. Herbert
Partner: UNT Libraries Government Documents Department
open access

Rough draft of Technical Data Summary covering preparation of initial Mark IIIA plates by extrusion cladding

Description: This Technical Data Summary comprises the technical information that has been developed to date for the preparation by extrusion cladding of the outer plate of the contemplated Mark IIIA fuel plate bundle. The Mark IIIA fuel bundle is designed to produce plutonium at higher power levels than is possible with the Mark I or Mark VII assemblies. The Mark IIIA and Mark V designs are being developed concurrently for the same purpose. The information, however, on the Mark IIIA design is at present fa… more
Date: June 22, 1956
Creator: O`Leary, W. J. & Herries, R. R.
Partner: UNT Libraries Government Documents Department
open access

On the Annealing and Aging of Zircaloy-3b

Description: The object of this study was to determine the effects of several annealing treatments and aging treatments on the tensile test behavior of Zircaloy-3b.
Date: October 22, 1956
Creator: Johnson, D. E.
Partner: UNT Libraries Government Documents Department
open access

Hazardous Materials - Redox Plant

Description: The Redox process uses or produces only a very few materials that are hazardous for reasons other than radioactivity. The conditions under which these materials become hazardous were carefully taken into consideration in the development of the process and design of the equipment. A considerable about of information on the hazardous properties of the process materials was obtained so that the pertinent material could be incorporated into the process specifications. Providing the equipment is ope… more
Date: May 22, 1956
Creator: Underwood, J. W.
Partner: UNT Libraries Government Documents Department
open access

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Description: The design criteria are written to supply information for the preparation of a project proposal covering budget item B-2265 for Fiscal Year 1956. The function of in-line instrumentation installed shall be the rapid on-the-spot analysis of process variables for quick presentation to process operators for immediate action in process control. Alarm or safety circuits may be incorporated on the equipment.
Date: February 22, 1956
Creator: Hildreth, N. T.
Partner: UNT Libraries Government Documents Department
open access

Fabrication Techniques and Heat-Transfer Results for Cast-Cored Air-Cooled Turbine Blades

Description: Memorandum presenting an investigation to devise an air-cooled turbine blade which eliminated the difficulties encountered with brazing in air-cooled-blade fabrication. Techniques were developed for casting air-cooled blades with a large number of relatively small cooling passages near the airfoil surface; two such blades of HS-21 material were operated in a turbojet engine modified for air cooling. Results regarding the heat-transfer characteristics, stress and durability results, and evaluati… more
Date: June 22, 1956
Creator: Freche, John C. & Oldrieve, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Effect of Inlet-Guide-Vane Angle on Performance Characteristics of a 13-Stage Axial-Flow Compressor in a Turbojet Engine

Description: Report presenting the effect of adjusting compressor inlet-guide-vane angle on overall compressor performance, stage performance, engine thrust, and specific fuel consumption in a 7000-pound-thrust turbojet engine. Data was obtained at several angles and demonstrated that increasing the guide-vane angle decreased the weight flow at the higher compressor speeds. It had no effect on stage performance other than at the first stage, where it reduced maximum flow, pressure, and temperature coefficie… more
Date: May 22, 1956
Creator: Medeiros, Arthur A. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Use of Area Suction to Increase the Effectiveness of Trailing-Edge Flaps of Various Spans on a Wing of 45 Degree Sweepback and Aspect Ratio 6

Description: Report discusses the results of an investigation of a model of a wing of 45 degree sweepback and aspect ratio 6 to determine the aerodynamic characteristics and suction requirements for boundary-layer control by means of area suction applied to trailing-edge flaps. Various flap spans and flap deflections were tested. The measured values of the coefficients were compared to the calculated values.
Date: June 22, 1956
Creator: Griffin, Roy N., Jr. & Hickey, David H.
Partner: UNT Libraries Government Documents Department
open access

Temperatures in a J47-25 turbojet-engine turbine section during steady-state and transient operation in an altitude test stand

Description: Report presenting a J47-25 engine instrumented with thermocouples and operated under steady-state and transient-conditions in an altitude test stand to determine the operating temperatures at altitude in the turbine section of a turbojet engine. Results regarding the temperature effects and transient operation are provided.
Date: May 22, 1956
Creator: Morse, C. R. & Johnston, J. R.
Partner: UNT Libraries Government Documents Department
open access

Investigation of two-stage counterrotating compressor I : design and over-all performance of transonic first compressor stage

Description: Report presenting a highly loaded transonic rotor which was designed, built, and tested as part of a two-stage counterrotating-compressor research program. The design conditions were chosen to explore the upper limits of loading and Mach number for the transonic unit. The complete rotor design procedure is presented as well as the recorded stall traces and techniques for obtaining the data.
Date: May 22, 1956
Creator: Wilcox, Ward W. & Wright, Linwood C.
Partner: UNT Libraries Government Documents Department
open access

Effect of fuels on screaming in 200-pound-thrust liquid-oxygen - fuel rocket engine

Description: Report presenting the tendencies of 14 different fuels and three fuel blends to produce high-frequency oscillatory combustion (screaming) in a 200-pound-thrust, water-cooled, liquid-oxygen-fuel rocket engine. The fuels, in order of increasing screaming tendency, were hydrazines, branched-chain paraffins, aromatics, and amines, and straight-chain paraffins. Results regarding screaming tendency and screaming amplitude are provided.
Date: June 22, 1956
Creator: Pass, Isaac & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Two-Stage Counterrotating Compressor. 3: Design of Second-Stage Rotor and Preliminary Over-All Performance

Description: At the design speed of a two-stage counterrotating compressor, an overall average pressure ratio of 4.3 was obtained at a specific weight flow of 27.2 pounds per second per square foot frontal area with an adiabatic efficiency of 0.75. Preliminary tests indicate that a weight-flow mismatching exists between the two rotors that causes the first rotor to operate at less than peak efficiency at design speed. At lower speeds, the first stage was forced to operate in the stalled region in single-sta… more
Date: October 22, 1956
Creator: Wilcox, Ward W. & Wright, Linwood C.
Partner: UNT Libraries Government Documents Department
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