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Altitude performance of J71-A-2(600-D1) turbojet engine

Description: From Introduction: "As part of a complete investigation of the J71-A-2(600-D1) turbojet engine conducted in an altitude test chamber at the NACA Lewis laboratory, the steady-state altitude performance, with afterburner inoperative and ejector shroud removed, was obtained and is presented herein. The component performance of the J71-A-2(600-D1) turbojet engine is presented in reference 1. The effects of compressor interstage bleed and adjustable inlet guide vanes on compressor-stall characteristics are described in reference 2."
Date: December 28, 1956
Creator: Smith, Ivan D. & Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department

APPR-1 Axial Non-Uniform Burn Up--Initial Studies

Description: The control rod position in relation to reactor lifetime and the relative concentrations of U/sup 235/ and B/sup 10/ as a function of U burned were found by a modified 2-group theory using the adjusted age and a straight 2- group theory without fast multiplication or resonance capture. Results indicate that at 15% average burnup the flux shape and reactivity do not vary appreciably from that given by the uniform analysis. (F.S.)
Date: March 28, 1956
Creator: Fairbanks, F. B.
Partner: UNT Libraries Government Documents Department

Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins

Description: An investigation of the use of fins to prevent high-frequency combustion-pressure oscillations (screaming) in the combustion chamber of a 1000-pound-thrust rocket engine with a chamber pressure of 300 pounds per square inch and using liquid oxygen and n-heptane as propellants. Tangential combustion-pressure oscillations were found to be eliminated with longitudinal fins located in the combustion zone. Results regarding engine performance, effect of fins, and destructiveness of screaming are provided.
Date: June 28, 1956
Creator: Priem, Richard J.
Partner: UNT Libraries Government Documents Department

Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane Rocket Engine With Longitudinal Fins

Description: Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.
Date: June 28, 1956
Creator: Priem, Richard J.
Partner: UNT Libraries Government Documents Department

A Bibliography of NACA Reports on Control of Turbojet Engines

Description: Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
Partner: UNT Libraries Government Documents Department

Component performance of J71-A-2(600-D1) turbojet engine at several Reynolds number indices

Description: Report presenting an investigation in the altitude test chamber to determine the altitude performance of the J71-A-2(600-D1) turbojet engine. The engine was equipped with two-position inlet guide vanes and compressor acceleration bleeds. Results regarding the compressor performance, combustor performance, turbine performance, and effect of altitude on engine performance are provided.
Date: December 28, 1956
Creator: Seashore, Ferris L. & Corrington, Lester C.
Partner: UNT Libraries Government Documents Department

Differential Thermal Analysis of Uranium Tetrafluoride-Uranium Dioxide Mixtures

Description: Abstract: "Approximate melting points have been determined for five samples of uranium tetrafluoride representing incompletely converted uranium dioxide and covering the range from about 2 to 20 w/o UO2, using the method of differential thermal analysis. The results indicate the melting temperatures are in the range of 920 to 980 C. No significant correlation between melting point and UO2 content was observed, possibly because of calcite formation. Similar results were obtained on synthetic mistakes of UF4 containing from 10 to 40 w/o UO2."
Date: June 28, 1956
Creator: Ewing, Robert A. & Bearse, Arthur E.
Partner: UNT Libraries Government Documents Department

Effect of a Fuselage on the Low-Speed Longitudinal Aerodynamic Characteristics of a 45 Degree Sweptback Wing with Double Slotted Flaps

Description: Memorandum presenting a low-speed investigation to determine the effect of a fuselage on the longitudinal aerodynamic characteristics of a 45 degree sweptback wing equipped with 0.35-semispan double slotted flaps. The wing had an aspect ratio of 3.7, a taper ratio of 0.41, and a streamwise thickness ratio of 0.086.
Date: September 28, 1956
Creator: Naeseth, Rodger L.
Partner: UNT Libraries Government Documents Department

Evaluation of Liquefied Hydrocarbon Gases as Turbojet Fuels

Description: Memorandum presenting an analysis of liquid methane, ethene, and propane along with normally liquid hydrocarbon fuels. The lower molecular weight hydrocarbons are superior to current JP-type fuels as heat sinks and that the more volatile fuels may be required with cooled-turbine engines.
Date: December 28, 1956
Creator: Hibbard, Robert R.
Partner: UNT Libraries Government Documents Department

Experimental and analytical investigation of an acceleration regulating control for a turbojet engine

Description: Report presenting an acceleration control that operates on fuel flow and uses directly measured acceleration as the control signal as applied to an axial-flow turbojet engine. A study to determine the feasibility and dynamic characteristics of the control was undertaken. Results regarding the open-loop characteristics and closed-loop characteristics are provided.
Date: June 28, 1956
Creator: Stiglic, Paul M.; Heppler, Herbert & Novik, David
Partner: UNT Libraries Government Documents Department

Experimental Investigation of a Transonic Axial-Flow-Compressor Rotor Designed for Sonic Inlet Velocity with an Inlet Hub-Tip Radius of 0.35

Description: Memorandum presenting a high-flow sonic-inlet compressor rotor employing double-circular-arc blade sections that was designed and tested in Freon-12. Results regarding overall performance, radial distribution, and blade-element performance are provided.
Date: September 28, 1956
Creator: Boxer, Emanuel & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

Formation of Radioactive Citrulline During PhotosyntheticC14O2-Fixation by Blue-Green Algae

Description: Citrilline has been isolated and identified from extracts of Nostoc muscorum. All members of the Cyanophyceae hitherto investigated show a relatively large amount of the CO fixed during photosynthesis in citrulline (ranging as high as 20% in Nostoc) when compared to the trace amounts found in the Chlorophyceae. Nostoc also has the ability to fix C{sup 14} in citrulline during dark fixation, but at a rate slower than in light. As no free urea or arginine was found in Nostoc, it is likely that citrulline is functioning in reactions other than those leading to arginine and urea synthesis. Other possible functions for citrulline are briefly discussed.
Date: August 28, 1956
Creator: Linko, Pekka; Holm-Hansen, O.; Bassham, J.A. & Calvin, M.
Partner: UNT Libraries Government Documents Department

Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Free-Flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Free-flight investigation over a Mach number range from 0.74 to 1.43 at lift coefficients from minus 0.15 to 0.75 of an airplane-configuration model having a 52.5 degree delta wing and a low swept horizontal tail

Description: Report presenting a free-flight investigation over a range of Mach numbers at a range of lift coefficients to determine the aerodynamic characteristics of an airplane-configuration model with a 52.5 degree delta wing and a low, swept horizontal tail. Results regarding time history, longitudinal trim, lift, drag, longitudinal static stability, side-force characteristics, and theoretical comparisons are provided.
Date: September 28, 1956
Creator: Kehlet, Alan B.
Partner: UNT Libraries Government Documents Department

Full-scale evaluation of some flameholder design concepts for high-inlet-velocity afterburners

Description: Report presenting an investigation of a full-scale afterburner with high burner-inlet velocity to determine burner performance with several variations in burner design. A total of 12 flameholder configurations were investigated at a specified burner-inlet velocity and a range of burner-inlet pressures. Results indicated that a basic annular two-V-gutter flameholder can operate at 90 to 95 percent combustion efficiency for fairly optimum burner length and pressure.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Partner: UNT Libraries Government Documents Department

Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Description: Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Partner: UNT Libraries Government Documents Department

Hanford Atomic Products Operation monthly report, August 1956

Description: This document presents a summary of work and progress at the Hanford Engineer Works for August 1956. 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 summarizes work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical, Radiological Sciences, Utilities and General Sciences, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.
Date: September 28, 1956
Partner: UNT Libraries Government Documents Department

Hinge Moment and Effectiveness of an Unswept Constant-Chord Control and an Overhang-Balanced, Swept Hinge-Line Control on an 80 Degree Swept Pointed Wing at Mach Numbers from 0.75 to 1.96

Description: Memorandum presenting an investigation of a semispan-wing-fuselage model with an 80 degree swept pointed wing with either an unbalanced constant-chord control or an overhang-balanced swept hinge-line control in the 9- by 12-inch blowdown tunnel. Control hinge moments and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 16 degrees at control deflections up to 25 degrees. Results regarding control effectiveness, control hinge moments, control drag, and evaluation of control characteristics are provided.
Date: August 28, 1956
Creator: Guy, Lawrence D.
Partner: UNT Libraries Government Documents Department