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open access

"25" Critically Consultation with J. W. Morfitt : April 3, 1950

Description: Summary: "Criticality was considered impossible in any contingency encountered in practice under either of the following conditions which include no safety factor: (a) In any isolated cylinder not more than 5 in. in disruptor, if the total amount of U235 present does not exceed 7.5 Eg. (b) In an isolated vessel of any shape and size, if the total amount of U235 present does not exceed 880 g. An "isolated" vessel is one which does not "see" more than 0.1 [...] other vessels containing fissionabl… more
Date: April 3, 1950
Creator: Merrill, E. T. & Sege, G.
open access

Abnormal Grain Growth in S-816 Alloy

Description: From Introduction: "This report presents the results obtained to date of an investigation to establish the fundamental causes of abnormal growth in S-816 alloy under conditions encountered during the forging of blades for the gas turbine of jet engines."
Date: April 1952
Creator: Rush, A. I.; Freeman, J. W. & White, A. E.
open access

Accuracy of Relaxation Length Measurements

Description: We consider here the accuracy of relaxation lengths measured during the water-uranium lattice experiments. Since such an analysis for all measurements would take a great deal of time, we have applied it to just one lattice. This one (2:1 water-to-metal ratio) was chosen completely at random.
Date: April 28, 1953
Creator: Kouts, H.
open access

The Accuracy of the Substitute-Stringer Approach for Determining the Bending Frequencies of Multistringer Box Beams

Description: "The accuracy of the substitute-stringer approach for including the effects of shear lag in the calculation of the transverse modes and frequencies of multistringer box beams is investigated. Box beams, the covers of which consist of normal-stress-carrying stringers on sheets which carry not only shear but also normal stress, are analyzed exactly. Frequencies of beams with various numbers of stringers, obtained by means of this exact analysis, serve to determine the possible accuracy of the fre… more
Date: April 1956
Creator: Davenport, William W.
open access

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Description: From Introduction: " Considerable analytical and experimental research has been done to find means of reducing the noise levels of the turbojet transports. Noise levels can be decreased by engine redesign to reduce the jet-exit velocity (ref. 1), proper flight-climb techniques (ref. 2), and the use of noise-suppression exhaust nozzles (refs. 3 to 5). The present report is concerned with the last method."
Date: April 1958
Creator: Ciepluch, Carl C.; North, Warren J.; Coles, Willard D. & Antl, Robert J.
open access

Adaptation of Combustion Principles to Aircraft Propulsion, Volume 1, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air

Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observ… more
Date: April 1, 1955
Creator: Barnett, Henry C. & Hibbard, Robert R.
open access

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.
Date: April 1950
Creator: Smith, Hamilton A. & Schaefer, Raymond F.
open access

The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures ar… more
Date: April 5, 1954
Creator: Runckel, Jack F. & Schmeer, James W.
open access

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Description: "Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose sec… more
Date: April 11, 1955
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
open access

Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Description: From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."
Date: April 25, 1955
Creator: Ulmann, Edward F. & Smith, Fred M.
open access

Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Description: Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = 1.41 in the 4- by 4-foot supersonic pressure tunnel. Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span wings for the cruciform delta wings and canard controls.
Date: April 12, 1954
Creator: Spearman, M. Leroy & Robinson, Ross B.
open access

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Description: "A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and … more
Date: April 11, 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
open access

Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96

Description: Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Date: April 24, 1956
Creator: Hadaway, William M.
open access

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 3: boundary layer and force measurements on a slender cone-cylinder body of revolution

Description: Report presenting an experimental investigation to determine the aerodynamic characteristics of a slender cone-cylinder body of revolution in the 1- by 1-foot supersonic wind tunnel. Viscous drag and three component forces were measured at Mach number 3.12 and a range of Reynolds numbers and angles of attack. Results regarding pressure distributions, boundary layer, and forces are provided.
Date: April 6, 1953
Creator: Jack, John R.
open access

Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of … more
Date: April 28, 1952
Creator: Kremzier, Emil J. & Dryer, Murray
open access

Aerosol Collection by Wetted Fiberglass Media

Description: A wet collection system for aerosols has been developed using fibrous media. Tests show the performance to be in accord with recently developed theory of collection by fibrous media. The effects of varying aerosol particle size, particle density, and gas velocity have indicated that inertial impaction is the primary collection mechanism. Three-year operating experience on several full scale plant installations shows reliable performance.
Date: April 28, 1954
Creator: Leary, Joseph A.; Clark, Robert A.; Hammond, R. Philip & Leopold, Charles S.
open access

Air Leakage Through Labyrinth Seals

Description: This report contains the results of tests which demonstrated the feasibility of using graphite labyrinth type seals, i.e., a bushing machined with alternate grooves and lands on the inside diameter to create a sufficient pressure drop to provide a satisfactory seal.
Date: April 8, 1955
Creator: McCarthy, P. B.
open access

Air Scattering of Co60 Gamma Rays: Theory Versus Experiment

Description: For Co60 source at 15 meters, the air-scattered gamma dose rate predicted by theory is excerpted from ORNL-1575, pp. 167-203. This is compared with experimental measurements for the same source and comparable geometry reported by Convair in CVAC-170T. After applying an appropriate correction for ground scattering as estimated in Mart-55-16T (Convair), the two results are found to be in substantial agreement.
Date: April 17, 1958
Creator: Moran, Rubert S.
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