High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels (open access)

High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels

Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.
Date: April 2, 1957
Creator: Kaufman, Harold R.
System: The UNT Digital Library
Resonance Absorption of Thorium (open access)

Resonance Absorption of Thorium

Abstract: Cadmium ratios for very thin (neutron and beta-wise) foils of thorium, gold, vanadium and indium have been measured in the glory hole of the WBNS. These cadmium ratios, together with the known thermal cross sections and a given calculated resonance integral for gold, were used to evaluare the resonance integrals of thorium, vanadium, and indium.
Date: April 2, 1953
Creator: Martin, D. H.
System: The UNT Digital Library
Organophosphorus Compounds in Rocket-Engine Applications (open access)

Organophosphorus Compounds in Rocket-Engine Applications

Report discussing the ignition-delay determinations of three organophosphorous fuels with nitric acid oxidants at simulated altitude conditions with a small-scale rocket engine.
Date: April 2, 1954
Creator: Ladanyi, Dezso J. & Hennings, Glen
System: The UNT Digital Library
Altitude Operation of Gas-Turbine Engine With Variable-Area Fuel-Nozzle System (open access)

Altitude Operation of Gas-Turbine Engine With Variable-Area Fuel-Nozzle System

From Introduction: "The investigation reported herein was therefore undertaken to extend this study to altitude conditions in which the low fuel-flow rates occur over the full range of engine speeds."
Date: April 2, 1951
Creator: Gold, H. & Rosenzweig, S.
System: The UNT Digital Library
The effects on the aerodynamic characteristics of varying the wing thickness ratio of a triangular wing-body configuration at transonic speeds from tests by the NACA wing-flow method (open access)

The effects on the aerodynamic characteristics of varying the wing thickness ratio of a triangular wing-body configuration at transonic speeds from tests by the NACA wing-flow method

Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of three triangular wing-fuselage models which differed only in wing thickness-chord ratio. The wings had an aspect ratio of 2.31 with 6-, 9-, and 12-percent-thick biconvex sections and a fuselage with a fineness ratio of 12. Results regarding the normal force, chord force, and pitching moment for various angles of attack.
Date: April 2, 1952
Creator: Hall, Albert W. & McKay, James M.
System: The UNT Digital Library
The Effect of a Change in Body Shape on the Loading of a 45 Degree Sweptback Wing-Body Combination at Transonic Speeds (open access)

The Effect of a Change in Body Shape on the Loading of a 45 Degree Sweptback Wing-Body Combination at Transonic Speeds

Memorandum presenting an investigation made in the 8-foot transonic tunnel of the pressure distribution on a wing-body combination with a 45 degree sweptback wing with aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The chordwise pressure distributions, which were determined at various spanwise stations, indicate that the flow about the two configurations is the same. Results regarding basic pressure measurements and loading and aerodynamic characteristics are provided.
Date: April 2, 1954
Creator: Loving, Donald L.
System: The UNT Digital Library
Aerodynamic characteristics of two flat-bottomed bodies at Mach number of 3.12 (open access)

Aerodynamic characteristics of two flat-bottomed bodies at Mach number of 3.12

From Introduction: "This report presents the results of an investigation in the NACA Lewis 1- by 1-foot supersonic wind tunnel of two flat-bottomed bodies to determine their aerodynamic characteristics at a Mach number of 3.12."
Date: April 2, 1954
Creator: Jack, John R. & Moskowitz, Barry
System: The UNT Digital Library
Preliminary Measurements of the Aerodynamic Yawing Derivatives of a Triangular, a Swept, and an Unswept Wing Performing Pure Yawing Oscillations, With a Description of the Instrumentation Employed (open access)

Preliminary Measurements of the Aerodynamic Yawing Derivatives of a Triangular, a Swept, and an Unswept Wing Performing Pure Yawing Oscillations, With a Description of the Instrumentation Employed

Report presenting an investigation to determine the effect of motion periodicity on the aerodynamic derivatives due to yawing velocity and yawing acceleration for a 60 degree delta wing, a 45 degree sweptback wing, and an unswept wing. Results were obtained from steady-state yawing-flow tests and tests of model performing pure sinusoidal yawing oscillations. Results regarding the static longitudinal characteristics, derivatives due to yawing velocity, and derivatives due to yawing acceleration are provided.
Date: April 2, 1956
Creator: Queijo, M. J.; Fletcher, Herman S.; Marple, C. G. & Hughes, F. M.
System: The UNT Digital Library
Investigation of Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 1.39 (open access)

Investigation of Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 1.39

Report presenting an investigation utilizing a blowdown-type tunnel to determine the effects of a propulsive jet on a zero angle-of-attack wing surface located in the vicinity of both a choked convergent nozzle and a convergent-divergent nozzle. Static-pressure surveys were made on a flat surface located in the vicinity of the propulsive jet. Results regaridng the jet-off and jet-on pressure coefficients, shock waves, and incremental normal force are provided.
Date: April 2, 1956
Creator: Bressette, Walter E. & Leiss, Abraham
System: The UNT Digital Library
Organophosphorus compounds in rocket-engine applications (open access)

Organophosphorus compounds in rocket-engine applications

Report presenting experimental ignition-delay determinations of mixed alkyl thiophosphites, triethyl trithiophsphite, and propylene N,N-dimethylamidophosphite with red and white fuming nitric acid conducted at a range of temperatures and pressure altitudes. The literature pertaining to the use of organo-phosphorous compounds in rocket-propellant combinations was surveyed and summarized with emphasis on ignition-delay investigations.
Date: April 2, 1954
Creator: Ladanyi, Dezso J. & Hennings, Glen
System: The UNT Digital Library
Three-dimensional transonic flow theory applied to slender wings and bodies (open access)

Three-dimensional transonic flow theory applied to slender wings and bodies

The present paper re-examines the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, giving special attention to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow, that is, flow at free-stream Mach number 1.
Date: April 2, 1956
Creator: Heaslet, Max A. & Spreiter, John R.
System: The UNT Digital Library
Fuselage side inlets : a study of some factors affecting their performance and a comparison with nose inlets (open access)

Fuselage side inlets : a study of some factors affecting their performance and a comparison with nose inlets

Report presenting basic principles affecting the performance of side-inlet air-induction systems as well as an examination of the performance of several fuselage side inlets and a comparison with nose inlets. Methods for improving the performance of both types of inlets are reviewed.
Date: April 2, 1956
Creator: Mossman, Emmet A.; Pfyl, Frank A. & Lazzeroni, Frank A.
System: The UNT Digital Library
The Solubility of Tributyl Phosphate in Aqueous Solutions (open access)

The Solubility of Tributyl Phosphate in Aqueous Solutions

Report describing a study regarding the solubility and related properties of tributyl phosphate (TBP), which has lower solubility in water than most uranium solvents. Pure TBP and TBP in an inert diluent were tested for solubility in water, several nitric acid solutions of varying concentrations, and other solutions typical of process streams. For TBP-diluent-water system tests, equilibrium water content in organic phase was found.
Date: April 2, 1951
Creator: Burger, Leland L. & Forsman, R. C.
System: The UNT Digital Library
Progress Relating to Civilian Applications During March, 1956 (open access)

Progress Relating to Civilian Applications During March, 1956

A report about elevated-temperature tensile properties of dilute uranium alloys. Alloys up to 2 a/o aluminum and 4 a/o zirconium have been fabricated to rod and are being tested at temperatures up to 500 C.
Date: April 2, 1956
Creator: Dayton, Russell W. & Tripton, Clyde R., Jr.
System: The UNT Digital Library
High-altitude performance investigation of J65-B-3 turbojet engine with both JP-4 and gaseous hydrogen fuels (open access)

High-altitude performance investigation of J65-B-3 turbojet engine with both JP-4 and gaseous hydrogen fuels

Report presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet and the ultimate blowout limit was at an altitude of about 75,000 feet. Combustion with hydrogen was found to be stable up to the facility altitude limit of 89,000 feet.
Date: April 2, 1957
Creator: Kaufman, Harold R.
System: The UNT Digital Library
Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet Engine (open access)

Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet Engine

"The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes between 15,000 and 66,000 feet in the Lewis altitude wind tunnel. Included in this study is a discussion of fuel nozzle coking, the altitude operating limits with and without the standard engine control, the compressor surge characteristics, and the engine starting and windmilling characteristics. Severe circumferential turbine outlet temperature gradients which occurred at high altitude as a result of fuel nozzle coking were alleviated by the manufacturer's change in the fuel flow divider schedule and in a nozzle gasket material" (p. 1).
Date: April 2, 1954
Creator: Wallner, Lewis E. & Saari, Martin J.
System: The UNT Digital Library
A Study of Second-Order Supersonic Flow Theory (open access)

A Study of Second-Order Supersonic Flow Theory

Second-order solutions of supersonic-flow problems are sought by iteration, using the linearized solution as the first step. For plane and axially symmetric flows, particular solutions of the iteration equation are discovered which reduce the second-order problem to an equivalent linearized problem. Comparison of second-order solutions with exact and numerical results shows great improvement over linearized theory.
Date: April 2, 1952
Creator: Van Dyke, Milton D.
System: The UNT Digital Library
The Synthetic Liquid Fuel Potential of Virginia (open access)

The Synthetic Liquid Fuel Potential of Virginia

Report documenting the suitability of Virginia for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.
Date: April 2, 1951
Creator: Ford, Bacon, and Davis
System: The UNT Digital Library
Operating Lives of Redox Mechanical Equipment (open access)

Operating Lives of Redox Mechanical Equipment

The operating lives of Redox Process mechanical equipment are given. Tables are included which give the operating hours, reason for failure, position, and original date installed.
Date: April 2, 1955
Creator: Stevenson, R. L.
System: The UNT Digital Library
Note on the Decay of Rb82 (open access)

Note on the Decay of Rb82

The purpose of this letter is to point out certain discrepancies between previous work on the decay of Rb82 (6.3 hour, B+, K-capture) and studies made recently at the University of California Radiation Laboratory.
Date: April 2, 1953
Creator: Easterday, Harry T.
System: The UNT Digital Library
Suggestion for High Pressure Letdown Device (open access)

Suggestion for High Pressure Letdown Device

A letdown valve design is described which reduces erosion of the sealing surfaces. It also provides for water flushing of the sealing surface before closing.
Date: April 2, 1957
Creator: Lyon, Richard Norton
System: The UNT Digital Library
Pressure Rise in HRT Shield Due to Reactor and Replacement heat Exchanger Rupture (open access)

Pressure Rise in HRT Shield Due to Reactor and Replacement heat Exchanger Rupture

.Recalculations were made of HRT cell pressures in the event of a simultaneous rupture of the reactor core vessel and the fuel and blanket heat exchangers. These calculations will be applicable after the replacement fuel heat exchanger is installed. The pressure rise in the cell is plotted as a function of time. A maximum cell pressure of 34 psig is achieved ~7 sec after rupture.
Date: April 2, 1957
Creator: Bolger, J. C.; Maak, R. O. & Gift, E. H.
System: The UNT Digital Library