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Dislocation Theory of the Fatigue of Metals
Description:
"A dislocation theory of fatigue failure for annealed solid solutions is presented. On the basis of this theory, an equation giving the dependence of the number of cycles for failure on the stress, the temperature, the material parameters, and the frequency is derived for uniformly stressed specimens. The equation is in quantitative agreement with the data" (p. 183).
Date:
September 12, 1947
Creator:
Machlin, E. S.
Partner:
UNT Libraries Government Documents Department
Analytical and Experimental Investigation of 90 Degrees Supersonic Turning Passages Suitable for Supersonic Compressors or Turbines
Description:
"Four 90 degree two-dimensional turning passages designed by the method of characteristics were tested at an inlet Mach number of 1.71. The measured losses varied from 5 to 15 percent of the inlet stagnation pressure. The smallest loss was obtained for a passage in which separation on the convex surface was minimized through the introduction of a favorable pressure gradient" (p. 1).
Date:
September 12, 1949
Creator:
Liccini, Luke L.
Partner:
UNT Libraries Government Documents Department
A comparison of the experimental subsonic pressure distributions about several bodies of revolution with pressure distributions computed by means of the linearized theory
Description:
Report presenting an analysis of the effects of compressibility on the pressure coefficients of several bodies of revolution by comparing experimentally determined pressure coefficients with corresponding pressure coefficients calculated by the use of linearized equations of compressible flow. The results indicated that the theoretical methods predict the subsonic pressure-coefficient changes over the central portion of the body but do not predict the pressure-coefficient changes near the nose.
Date:
September 12, 1949
Creator:
Matthews, Clarence W.
Partner:
UNT Libraries Government Documents Department
Hydrodynamic characteristics of a swept planing-tail hull
Description:
Report presenting the hydrodynamic characteristics of a swept planing-tail hull as determined by water tank testing. The hull shape was based on results from previous testing indicating that symmetrical airfoil sections and slender boom-like afterbodies lower the drag. Results regarding spray characteristics, take-off stability and trims, landing stability, resistance, and directional stability are presented.
Date:
September 12, 1949
Creator:
McKann, Robert E.; Coffee, Claude W. & Arabian, Donald D.
Partner:
UNT Libraries Government Documents Department
Life of Van Stone Corrective Measures
Description:
This report is a document summarizing all information available on life aspects of various measures proposed to reduce or eliminate corrosion of Van Stone flanger.
Date:
September 12, 1949
Creator:
Botsford, C. W. & Eschbach, E. A.
Partner:
UNT Libraries Government Documents Department
Preliminary analysis of axial-flow compressors having supersonic velocity at the entrance of the stator
Description:
Report presenting a supersonic compressor design with supersonic velocity at the entrance of the stator on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The starting conditions and stability of the flow in rotor and stator are discussed, and the desirability of the variable-geometry stators and adjustable guide vanes is indicated.
Date:
September 12, 1949
Creator:
Ferri, Antonio
Partner:
UNT Libraries Government Documents Department
Preliminary Analysis of Axial-Flow Compressors Having Supersonic Velocity at the Entrance of the Stator
Description:
"A supersonic compressor design having supersonic velocity at the entrance of the stator is analyzed on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The results of the analysis show that compression ratios per stage of 6 to 10 can be obtained with adiabatic efficiency between 70 and 80 percent. Consideration is also given in the analysis to the starting, stability, and range of effic…
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Date:
September 12, 1949
Creator:
Ferri, Antonio
Partner:
UNT Libraries Government Documents Department
Preliminary Wind-Tunnel Investigation at High-Subsonic Speeds of Planing-Tail, Blended, and Airfoil-Forebody Swept Hulls
Description:
Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the high-subsonic aerodynamic characteristics of three different types of flying-boat hull: a planing-tail hull, a blended hull, and an airfoil-forebody swept hull.
Date:
September 12, 1949
Creator:
Riebe, John M. & MacLeod, Richard G.
Partner:
UNT Libraries Government Documents Department
Stepwise Calculation for the Determination of the Number of Transfer Units in Countercurrent Extraction Columns
Description:
Report discussing a method for the stepwise calculation of the number of transfer units utilized in a given solvent extraction operation. "Use of the method results in a very appreciable saving in time of calculation with an error of 1.5% for the runs tested. The error tends to become smaller with increasing total numbers of transfer units involved."
Date:
September 12, 1949
Creator:
Burns, W. A. & Eschbach, E. A.
Partner:
UNT Libraries Government Documents Department
Systematics of Alpha-Radioactivity
Description:
Correlations of alpha-decay energies in terms of mass number and atomic number have been made for all of the alpha-emitting species now numbering over 100. For each element isotopes show increase in alpha-energy with decrease in mass number except in the region of 126 neutrons where there is an explainable reversal. This reversal has the effect of creating a region of relatively low alpha-energy and long half-life at low mass numbers for such elements as astatine, emanation, francium, and possi…
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Date:
September 12, 1949
Creator:
Perlman, I.; Ghiorso, A. & Seaborg, G. T.
Partner:
UNT Libraries Government Documents Department
A comparison of theory and experiment for high-speed free-molecule flow
Description:
A comparison is made of free-molecule-flow theory with the results of wind-tunnel tests performed to determine the drag and temperature-rise characteristics of a transverse circular cylinder. The measured values of the cylinder center-point temperature confirmed the salient point of the heat-transfer analysis which was the prediction that an insulated cylinder would attain a temperature higher than the stagnation temperature of the stream. Good agreement was obtained between the theoretical and…
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Date:
September 12, 1950
Creator:
Stalder, Jackson R.; Goodwin, Glen & Creager, Marcus O.
Partner:
UNT Libraries Government Documents Department
Flight Measurements of the Pressure Distribution on the Wing of the X-1 Airplane (10 Percent Thick Wing) Over a Chordwise Station Near the Midspan, in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull Up at a Mach Number of 0.98
Description:
Report presenting measurements of chordwise pressure distribution over the 10-percent-thick wing of the X-1 research airplane at a section near the midspan of the left wing. Results regarding the upper- and lower-surface pressure distributions at a range of Mach numbers and section loads are provided.
Date:
September 12, 1950
Creator:
Carner, H. Arthur & Knapp, Ronald J.
Partner:
UNT Libraries Government Documents Department
Lift and pitching-moment interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02
Description:
Report investigating the effects of interference on wing-body combinations by testing a pointed, cylindrical body at Mach numbers of 1.50 and 2.02 of six triangular wings with a range of aspect ratios and with the wing and body in combination. Theoretical characteristics of the body and wings alone and in combination were calculated from available theories and compared with experimental results.
Date:
September 12, 1950
Creator:
Nielsen, Jack N.; Katzen, Elliott D. & Tang, Kenneth K.
Partner:
UNT Libraries Government Documents Department
A numerical method for the stress analysis of stiffened-shell structures under nonuniform temperature distributions
Description:
A numerical method is presented for the stress analysis of stiffened-shell structures of arbitrary cross section under nonuniform temperature distributions. The method is based on a previously published procedure that is extended to include temperature effects and multicell construction. The application of the method to practical problems is discussed and an illustrative analysis is presented of a two-cell box beam under the combined action of vertical loads and a nonuniform temperature distrib…
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Date:
September 12, 1950
Creator:
Heldenfels, Richard R.
Partner:
UNT Libraries Government Documents Department
Zirconium Purification Pilot Plant
Description:
This report discusses the process of zirconium purification, providing an alternate method for converting ZrCl4 solution to the oxide in order to free it from small amounts of hafnium impurity that are naturally present.
Date:
September 12, 1950
Creator:
Lea, D. C.; Aykanian, A. A.; Abbanat, R. G. & Bowman, W. H.
Partner:
UNT Libraries Government Documents Department
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures
Description:
"An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is …
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Date:
September 12, 1951
Creator:
Long, Roger A. & Esgar, Jack B.
Partner:
UNT Libraries Government Documents Department
A flight evaluation of the longitudinal stability characteristics associated with the pitch-up of a swept-wing airplane in maneuvering flight at transonic speeds
Description:
This report presents the results of flight measurements of longitudinal stability and control characteristics made on a swept-wing jet aircraft to determine the origin of the pitch-up encountered in maneuvering flight at transonic speeds. For this purpose measurements were made of elevator angle, tail angle of attack, and wing-fuselage pitching moments (obtained from measurements of the balancing tail loads).
Date:
September 12, 1951
Creator:
Anderson, Seth B. & Bray, Richard S.
Partner:
UNT Libraries Government Documents Department
Investigation at Mach number 1.91 of side and base pressure distributions over conical boattails without and with jet flow issuing from base
Description:
Experimental side and blade pressure distributions over a series of conical boattails without and with jet flow from the base are presented at a Mach number of 1.91. For the case of no jet flow the methods of characteristics and linearized theory are shown to overpredict the side pressure drag. A semi-empirical theory is presented to predict the effect of boattail angle on base pressure. With the boattail extending to a sharp edge at the nozzle exit, the over-pressure jet is shown to decrease t…
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Date:
September 12, 1951
Creator:
Cortright, Edgar M., Jr. & Schroeder, Albert H.
Partner:
UNT Libraries Government Documents Department
A Method for the Design of Sweptback Wings Warped to Produce Specified Flight Characteristics at Supersonic Speeds
Description:
Memorandum presenting a method for designing a wing to be self-trimming at a given set of flight conditions. The spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag. The procedure is illustrated using several examples.
Date:
September 12, 1951
Creator:
Tucker, Warren A.
Partner:
UNT Libraries Government Documents Department
Water Landing Investigation of a Hydro-Ski Model at Beam Loadings of 18.9 and 4.4
Description:
Report presenting an investigation of water landings in the impact basin with a model with a flat rectangular planing surface, a pulled-up bow, and a simulated landing wheel. Runs were made at several wave conditions, trim ranges, flight-path angles, and beam loadings. The results were found to be applicable in predicting loads and motions exhibited by a flat rectangular ski during impact with a water surface.
Date:
September 12, 1951
Creator:
Batterson, Sidney A.
Partner:
UNT Libraries Government Documents Department
Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane
Description:
Report presenting tests to investigate the use of a simple centering spring, which had no variation of force gradient with impact pressure, as an artificial feel device for the elevator control of a fighter airplane. Testing was conducted using a Chance Vought F4U-4B airplane equipped with power controls. Results regarding the force experienced and effects of the feel system are provided.
Date:
September 12, 1952
Creator:
Adams, James J. & Whitten, James B.
Partner:
UNT Libraries Government Documents Department
The Thermal Neutron Cross Section Of 9.2h Xe^135
Description:
In this report it reviews a possible declassification of the content of report CP-2782 (February 15, 1945) that presents the data of the most careful measurements of the thermal neutron cross section of 9.2h Xe^135 and re-evaluation of the particular methods of measuring neutron flux employed in this experiment had been made for other purposes.
Date:
September 12, 1952
Creator:
Freedman, M.S.
Partner:
UNT Libraries Government Documents Department
THE HYDROLYSIS OF THE COMPOUND OF POTASSIUM WITH IRRADIATED GRAPHITE
Description:
Potassium, the reaction product of graphite with potassium, and the reaction product of irradiated graphite with potassium were subjected to hydrolysis. The gases evolved from the respective samples were analyzed mass spectroscopically. Hydrocarbons (methane and a trace of ethane) were found in the gas evolved from the irradiated graphite compound only, and the quantity was about that which would have been expected from the number of non-aggregated displaced atoms. The result was obtained for a…
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Date:
September 12, 1955
Creator:
Primak, W.L. & Quarterman, L.A.
Partner:
UNT Libraries Government Documents Department
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