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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Study of the Feasibility of Aqueous Recovery of Spent Fuels. Part 3. Calculated Distribution of Fission Product Nuclides.

Study of the Feasibility of Aqueous Recovery of Spent Fuels. Part 3. Calculated Distribution of Fission Product Nuclides.

Date: June 1954
Creator: Nehemias, John V.
Description: Calculation of evaluation of the mass and the activity of each fission product nuclide present in the spent fuel of a 500 Mw reactor operating on a 42 day cycle, at the time of removal from the reactor and as a function of time thereafter.
Contributing Partner: UNT Libraries Government Documents Department
A study of the flow over a 45 degree sweptback wing-fuselage combination at transonic Mach numbers

A study of the flow over a 45 degree sweptback wing-fuselage combination at transonic Mach numbers

Date: June 25, 1952
Creator: Whitcomb, Richard T & Kelly, Homas C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the high-speed performance characteristics of 90 degrees bends in circular ducts

A study of the high-speed performance characteristics of 90 degrees bends in circular ducts

Date: June 1, 1956
Creator: Higginbotham, James T; Wood, Charles C & Valentine, E Floyd
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the impact behavior of high-temperature materials

A study of the impact behavior of high-temperature materials

Date: March 1, 1957
Creator: Probst, H B & Mchenry, Howard T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of the Micro-Nonuniformity of the Plastic Deformation of Steel

Study of the Micro-Nonuniformity of the Plastic Deformation of Steel

Date: August 1, 1957
Creator: Chechulin, B. B.
Description: The plastic flow during deformation of real polycrystalline metals has specific characteristics which distinguish the plastic deformation of metals from the deformation of ordinary isotropic bodies. One of these characteristics is the marked micro-nonuniformity of the plastic deformation of metals. P.O. Pashkov demonstrated the presence of a considerable micro-nonuniformity of the plastic deformation of coarse-grained steel wit medium or low carbon content. Analogous results in the case of tension of coarse-grained aluminum were obtained by W. Boas, who paid particular attention to the role of the grain boundaries in plastic flow. The nonuniformit of the plastic deformation in microvolumes was also recorded by T.N. Gudkova and others, on the alloy KhN80T. N.F. Lashko pointed out the nonuniformity of the plastic deformation for a series of pure polycrystalline metals and one-phase alloys. In his later reports, P.O. Pashkov arrives at he conclusion that the nonuniformity of the distribution of the deformation along the individual grains has a significant effect on the strength and plastic characteristics of polycrystalline metals in the process of plastic flow. However, until now there has not existed any systematic investigation of the general rules of the microscopic nonuniformit of plastic deformation even though the real polycrystalline metals ...
Contributing Partner: UNT Libraries Government Documents Department
Study of the mixture distribution of a double-row radial aircraft engine

Study of the mixture distribution of a double-row radial aircraft engine

Date: October 1, 1945
Creator: Hickel, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of the momentum distribution of turbulent boundary layers in adverse pressure gradients

Study of the momentum distribution of turbulent boundary layers in adverse pressure gradients

Date: January 1, 1955
Creator: Sandborn, Virgil A & Slogar, Raymond J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

Date: January 1, 1958
Creator: Allen, H Julian & Eggers, A J , Jr
Description: A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
Contributing Partner: UNT Libraries Government Documents Department
A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds

A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds

Date: October 1, 1957
Creator: Allen, Julian H & Eggers, A J , Jr
Description: A simplified analysis of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
Contributing Partner: UNT Libraries Government Documents Department
A Study of the Motion and Aerodynamic Heating of Missiles Entering the Earth's Atmosphere at High Supersonic Speeds

A Study of the Motion and Aerodynamic Heating of Missiles Entering the Earth's Atmosphere at High Supersonic Speeds

Date: August 25, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Description: A simplified analysis is made of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds. It is found that, in general, the gravity force is negligible compared to the aerodynamic drag force and, hence, that the trajectory is essentially a straight line. A constant drag coefficient and an exponential variation of density with altitude are assumed and generalized curves for the variation of missile speed and deceleration with altitude are obtained. A curious finding is that the maximum deceleration is independent of physical characteristics of a missile (e.g., mass, size, and drag coefficient) and is determined only by entry speed and flight-path angle, provided this deceleration occurs before impact. This provision is satisfied by missiles presently of more usual interest.
Contributing Partner: UNT Libraries Government Documents Department
Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels

Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels

Date: January 6, 1954
Creator: Pinns, Murray L & Goodman, Irving A
Description: Magnesium-hydrocarbon slurries containing a moderate proportion of petrolatum have physical properties such that they offer promise as experimental aircraft fuels. The settling of the magnesium is greatly retarded by the petrolatum, and the slurries can easily be remixed to their original condition after storage. Successive batches which have closely similar properties can be prepared readily. The apparent viscosity of these slurries increased rapidly with increasing magnesium concentration, with increasing petrolatum concentration, and with decreasing temperature. As the apparent viscosity increased, the extent of settling and the ease of remixing both decreased. Although no quantitative correlation was found between the properties of the slurry and those of the petrolatum, and no one petrolatum gave slurries which were best in all respects, one of the five petrolatum used was judged to be superior to the others.
Contributing Partner: UNT Libraries Government Documents Department
A study of the pitching moments and the stability characteristics of monoplanes

A study of the pitching moments and the stability characteristics of monoplanes

Date: November 1, 1934
Creator: Higgins, George J
Description: This note presents a study of the pitching moments and the stability characteristics of monoplanes. Expressions for the pitching-moment coefficient and the Diehl stability coefficient for the monoplane are developed, suitable for the use of airplane designers. The effective difference between the high-wing and low-wing types is portrayed and discussed. Comparisons between experimental and computed values are made. Charts for use in the solution of numerical values of the pitching-moment and stability coefficients are presented.
Contributing Partner: UNT Libraries Government Documents Department
Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers

Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers

Date: May 5, 1952
Creator: Donaldson, Coleman Dup & Lange, Roy H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers

Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers

Date: September 1, 1952
Creator: Donaldson, Coleman Dup & Lange, Roy H
Description: Results are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2 x 10 (sup) 6 to 19 x 10 (sup) 6. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain practical design problems.
Contributing Partner: UNT Libraries Government Documents Department
A study of the problem of designing airplanes with satisfactory inherent damping of the dutch roll oscillation

A study of the problem of designing airplanes with satisfactory inherent damping of the dutch roll oscillation

Date: January 1, 1954
Creator: Campbell, John P & Mckinney, Marion O , Jr
Description: Considerable interest has recently been shown in means of obtaining satisfactory stability of the dutch roll oscillation for modern high-performance airplanes without resort to complicated artificial stabilizing devices. One approach to this problem is to lay out the airplane in the earliest stages of design so that it will have the greatest practicable inherent stability of the lateral oscillation. The present report presents some preliminary results of a theoretical analysis to determine the design features that appear most promising in providing adequate inherent stability. These preliminary results cover the case of fighter airplanes at subsonic speeds. The investigation indicated that it is possible to design fighter airplanes to have substantially better inherent stability than most current designs. Since the use of low-aspect-ratio swept-back wings is largely responsible for poor dutch roll stability, it is important to design the airplane with the maximum aspect ratio and minimum sweep that will permit attainment of the desired performance. The radius of gyration in roll should be kept as low as possible and the nose-up inclination of the principal longitudinal axis of inertia should be made as great as practicable. (author).
Contributing Partner: UNT Libraries Government Documents Department
A Study of the Production of Well-Characterized Aerosols Using a Flow Reactor

A Study of the Production of Well-Characterized Aerosols Using a Flow Reactor

Date: December 1977
Creator: Zygmunt, Roger W.
Description: Investigation of five factors affecting the aerosol generation in a glass frit bubbler system.
Contributing Partner: UNT Libraries Government Documents Department
A study of the radiation from laminar and turbulent open propane-air flames as a function of flame area, equivalence ratio, and fuel flow rate

A study of the radiation from laminar and turbulent open propane-air flames as a function of flame area, equivalence ratio, and fuel flow rate

Date: August 24, 1954
Creator: Clark, Thomas P & Bittker, David A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of the resistance offered by propellers rotating on an airstream

Study of the resistance offered by propellers rotating on an airstream

Date: January 1, 1921
Creator: Lame, M
Description: This report presents a series of tests conducted to verify the formula for thrust P = q(exp 2) D(exp 2) V(exp 2), where P represents thrust, V the velocity of the airstream, D the diameter of the propeller, and q the lifting quality of a comparative propeller which is called the conjugate propeller.
Contributing Partner: UNT Libraries Government Documents Department
A study of the stability of the incompressible laminar boundary layer on infinite wedges

A study of the stability of the incompressible laminar boundary layer on infinite wedges

Date: August 1, 1953
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the stability of the laminar boundary layer as affected by changes in the boundary-layer thickness in regions of pressure gradient and flow through the surface

A study of the stability of the laminar boundary layer as affected by changes in the boundary-layer thickness in regions of pressure gradient and flow through the surface

Date: August 1, 1952
Creator: Tetervin, Neal & Levine, David A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of the State-of-the-Art of Instrumentation for Process Control and Safety in Large-Scale Coal Gasification, Liquefaction, and Fluidized-Bed Combustion Systems

Study of the State-of-the-Art of Instrumentation for Process Control and Safety in Large-Scale Coal Gasification, Liquefaction, and Fluidized-Bed Combustion Systems

Date: 1976
Creator: O'Fallon, N. M.; Beyerlein, R. A.; Managan, W. W.; Karplus, H. B. & Mulcahe, T. P.
Description: A study has been carried out to determine the state-of-the-art of instrumentation which is available for process control and safety in planned demonstration and commercial scale coal gasification, liquefaction, and fluidized-bed combustion systems. The study identified available instrumentation which will perform satisfactorily in these systems and pinpointed deficiencies for which instruments must be developed. The identified deficiencies fall into the same few categories for all processes considered. These categories are presented with associated physical parameters found in the various processes studied. Development of instruments to meet these deficiencies is recommended along with development of control valves and optimal control schemes in order to assure the possibility of automatic control of the large scale coal conversion and combustion systems.
Contributing Partner: UNT Libraries Government Documents Department
Study of the subsonic forces and moments on an inclined plate of infinite span

Study of the subsonic forces and moments on an inclined plate of infinite span

Date: June 1, 1954
Creator: Wick, Bradford H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of the supersonic propeller

Study of the supersonic propeller

Date: March 1, 1953
Creator: Fabri, Jean & Siestrunck, Raymond
Description: In this paper a propeller having all sections operating at supersonic speeds is designated a supersonic propeller regardless of flight speed. Analyses assume subsonic flight speeds but very high rotational speeds. A very elementary analysis of the efficiency of a jet-propeller system is presented. A propeller analysis based on conventional vortex blade element theory is presented and reduced to a single point method which leads to an expression for optimum advance ratio in terms of hub-tip diameter ratio and airfoil fineness ratio. An expression for propeller efficiency in terms of advance ratio, hub-tip diameter ratio, and airfoil thickness ratio is also presented. Use is made of theoretical airfoil characteristics at supersonic speeds. A study of blade section interference, blade shock and expansion fields, at supersonic section speeds is presented. An example taken indicates that an efficiency of seventy percent can be obtained with a propeller having a tip Mach number of 2.3.
Contributing Partner: UNT Libraries Government Documents Department
A study of the tightness and flushness of machine-countersunk rivets for aircraft

A study of the tightness and flushness of machine-countersunk rivets for aircraft

Date: June 1, 1942
Creator: Gottlieb, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department