Resource Type
Serial/Series Title
NACA Research Memorandums
27
Oak Ridge National Laboratory Reports
4
Atomic Energy Commission Reports
3
CF (Series)
3
University of California Radiation Laboratory Reports
3
HW (Series)
1
Hanford Works Reports
1
Health and Safety Laboratory Reports
1
Homogeneous Reactor Project Quarterly Progress Report
1
ORNL (Series)
1
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Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine
From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date:
August 19, 1957
Creator:
Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
System:
The UNT Digital Library
Design and performance of flight-type liquid-hydrogen heat exchanger
Report presenting an investigation of a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. The heat exchanger was evaluated in an altitude test chamber in conjunction with the complete aircraft fuel system. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date:
August 19, 1957
Creator:
Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
System:
The UNT Digital Library
Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System
Memorandum presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The fuel system was designed to investigate some of the problems associated with the utilization of hydrogen as an aircraft fuel. Speed control of the engine was obtained by coupling the hydrogen regulator to the JP-4 fuel control.
Date:
August 19, 1957
Creator:
Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
System:
The UNT Digital Library
Flight Investigation of a Liquid Hydrogen Fuel System
Memorandum presenting testing of a twin-engine light bomber modified to utilize hydrogen fuel in one of the two engines during flight at an altitude of 50,000 feet. Three completely successful flights were made using hydrogen fuel. Data are presented to show the effect of tank agitation on fuel pressure and fuel losses.
Date:
August 19, 1957
Creator:
Mulholland, Donald R.; Acker, Loren W.; Christenson, Harold H. & Gough, William V.
System:
The UNT Digital Library
Some Aspects of the Research on Transcurium Elements at Berkeley
Report discussing the personal aspects involved in the research on transcurium elements at the Lawrence Radiation Laboratory, as well as a brief summary of previously unpublished work with heavy ions.
Date:
April 19, 1957
Creator:
Thompson, Stanley Gerald, 1912-1976
System:
The UNT Digital Library
A Description of a Shock Wave in Free Particle Hydrodynamics with Internal Magnetic Fields
Abstract: "The structure of an extremely strong magnetohydrodynamic shock is discussed in the limit of no particle collisions. It is tentatively concluded that the shock transition takes place through the mechanism of a strong electric field produced by charge separation. The pressure in the shocked plasma is due primarily to a very high electron temperature. The ions, on the other hand, undergo an irreversible temperature change of only 3."
Date:
February 19, 1957
Creator:
Colgate, Stirling A.
System:
The UNT Digital Library
A Special Purpose Slide Rule for Computing Solid Angles
Abstract: The design and construction of a slide rule for calculating the solid angle subtended by a rectangle at a point located on a line perpendicular to the center of the rectangle are described.
Date:
September 19, 1957
Creator:
Knight, J. R. & Henry, H. F.
System:
The UNT Digital Library
Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
Date:
February 19, 1957
Creator:
Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
System:
The UNT Digital Library
Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power
Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.
Date:
December 19, 1957
Creator:
Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
System:
The UNT Digital Library
Comparative Study of Turbofan and Turbojet Engines
Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
Date:
July 19, 1957
Creator:
Kaufman, Harold R.; Benser, William A. & Gabriel, David S.
System:
The UNT Digital Library
An Investigation at Low Speed of the Spin Instability of Mortar-Shell Tails
An investigation was made in the Langley stability tunnel to study the influence of number of fins, fin shrouding, and fin aspect ratio on the spin instability of mortar-shell tail surfaces. It was found that the 12-fin tails tested spun less rapidly throughout the angle-of-yaw range than did the 6-fin tails and that fin shrouding reduced the spin encountered by a large amount.
Date:
June 19, 1957
Creator:
Bird, John D. & Lichtenstein, Jacob H.
System:
The UNT Digital Library
Investigation of an Underslung Normal-Wedge Inlet at Free-Stream Mach Numbers From 1.50 to 1.99
Wedge and scoop air inlet performance and thrust minus drag comparisons at free stream in supersonic wind tunnel test.
Date:
March 19, 1957
Creator:
Vargo, Donald J. & Weinstein, Maynard I.
System:
The UNT Digital Library
Factors Affecting Loads at Hypersonic Speeds
Report presenting a brief summary of current loads information at hypersonic speeds and some ways of estimating the loads on aircraft components when designing an aircraft.
Date:
June 19, 1957
Creator:
Henderson, Arthur, Jr. & Bertram, Mitchel H.
System:
The UNT Digital Library
Die Design for Hot Presses ; [Bibliography]
Abstract: "This is a selective bibliography of books and periodical articles relating to die design of hot presses. Sources consulted include: ASM Review of Metal Literature, 1950-1954; Chemical Abstracts, 1950-1055; Engineering Index, 1950-1055; Industrial Arts Index, 1950-March 1957; Metallurgical Abstracts, 1950-1953; Nuclear Science Abstracts, 1950-March 1957; Physics Abstracts, 1950-1955; the library card catalog, and the Technical Information Division AEC card catalog."
Date:
April 19, 1957
Creator:
U.S. Atomic Energy Commission
System:
The UNT Digital Library
Report on the Texas Company radioactivity survey and evaluation by AEC test drilling in the Blanding area, July-October 1951
A memorandum report on test drilling of areas of anomalous radioactivity.
Date:
April 19, 1957
Creator:
Melancon, Paul E.; Dressner, Elliott F. & Bailey, Judith H.
System:
The UNT Digital Library
Transistorization of Nuclear Counting Circuits
From Abstract: "The advantage of long operational life, low power drain and miniaturization may be realized in nuclear counting circuits through the use of transistors. The disadvantage of instability, due to the effects of temperature change in the transistor, may be minimized in counting circuit designs. Representative circuits of a binary stage, amplitude discriminator, one shot multivibrator, and ratemeters are included. These were designed using the criteria of an minimum Beta and a maximum Ico."
Date:
August 19, 1957
Creator:
Graveson, R. T. & Sadowski, H.
System:
The UNT Digital Library
Examination of Donut on Rupture Slug No. 14
Pursuant to Dr. Kingdon's request for specific information concerning the donut pictured on pages 26-29 of WAPD-64, a close examination of this defect on Failure No. 14 was made. The slug was examined through 10 inches of Pb-glass and photographs were made. A clay impression of the surface area containing the donut was obtained, and using this impression, an Armstrong's Adhesive replica of this can wall surface area was cast.
Date:
February 19, 1957
Creator:
O'Keefe, D. P.
System:
The UNT Digital Library
Homogeneous Reactor Project Quarterly Progress Report: August-October 1956
Report issued by the Oak Ridge National Laboratory discussing quarterly progress made by the Homogeneous Reactor Program. Descriptions of progress and studies conducted are presented. This report includes tables, illustrations, and photographs.
Date:
February 19, 1957
Creator:
Briggs, R. B.; Winters, C. E.; Beall, S. E.; Lane, J. A.; Bohlmann, E. G.; Bruce, F. R. et al.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Static Lateral and Longitudinal Stability Characteristics of a 1/62-Scale Model of the X-1E Airplane at Combined Angles of Attack and Sideslip at Supersonic Speeds
Report presenting an investigation to determine the static longitudinal and lateral stability characteristics of a model of X-1E airplane at combined angles of attack and sideslip. Results regarding the static longitudinal and lateral force and moment characteristics and stability derivatives are provided.
Date:
September 19, 1957
Creator:
Henderson, Arthur, Jr.
System:
The UNT Digital Library
Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0
Report presenting the results of an investigation to determine the effects of conical camber on the lift, drag, and pitching-moment characteristics of a wing-body combination with a triangular wing of aspect ratio 3.0. At subsonic speeds, the use of camber was found to result in substantial reductions in drag coefficients at lift coefficients above 0.15.
Date:
February 19, 1957
Creator:
Peterson, Victor L. & Boyd, John W.
System:
The UNT Digital Library
Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System
Report presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The system was designed to explore some problems associated using hydrogen as an aircraft fuel. Results regarding the steady-state response, transient response, and performance in engine-speed loop for the system are provided.
Date:
August 19, 1957
Creator:
Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
System:
The UNT Digital Library
Design and performance of flight-type liquid-hydrogen heat exchanger
Report presenting a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. A ram-air heat exchanger was used to vaporize liquid hydrogen. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date:
August 19, 1957
Creator:
Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
System:
The UNT Digital Library
Effect of Full-Span Trailing-Edge Elevons on the Transonic Longitudinal Aerodynamic Characteristics of a Wing-Body Combination Having a 3-Percent-Thick Triangular Wing With 60 Degree Leading-Edge Sweep
Report presenting the results of an investigation to determine the effects of full-span trailing-edge flaps on the static longitudinal characteristics of a triangular wing-body combination. Data was obtained for the basic configuration and for a wing with the control surfaces deflected for longitudinal control.
Date:
September 19, 1957
Creator:
Critzos, Chris C. & Foss, Willard E., Jr.
System:
The UNT Digital Library
Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From Unswept-, Sweptback-, and Modified-Delta-Wing-Fuselage Combinations at Zero Sideslip
Report presenting an investigation in the high-speed tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from midsemispan locations of various types of wings. The purpose of the investigation is to determine the nature and origin of the mutual interference experienced by various combinations of wing-fuselage models and externally carried missiles. Results regarding isolated missile characteristics, the effect of varying chordwise position, effects of angle of attack and Mach number, effect of airplane wing geometric characteristics, effect of missile spanwise location, and comparison of wing-fuselage and fuselage effects on the missile forces and moments are provided.
Date:
March 19, 1957
Creator:
Alford, William J., Jr. & King, Thomas J., Jr.
System:
The UNT Digital Library