Optimization of Power-Plant and Airplane Performance—a Symposium. Aeronautical Engineering Review, vol. 13, June 1954, pp. 42-56. The Compound Aero Engine, by E. E. Chatterton, Aeronautics, vol. 30, June 1954, pp. 61-62, 67-68, 71. Characteristics of a Vaporizing Combustor for Aviation Gas Turbines, by W. D. Pouchot and J. R. Hamm, Trans. ASME, vol. 76, July 1954, pp. 801-807. Contribution to the Study of Axial Supersonic Compressors, by Pierre Schwaar, ZAMP, vol. 5, Mar. 15, 1954, pp. 13615 (in French). Applications of Dimensional Analysis to Spray-Nozzle Performance Data, by R. Shafer and Harry L. Bovey, / . Res. Nat. Bur. Stand., vol. 52, March 1954, pp. 141-147. Gas Turbine Starters for Jet Engines, by L. R. Neurlin and F . W. Fernald, Aviation Age, vol. 21, May 1954, pp. 138146. The Future of the Turbo Compound Engine, by Russell R. Mock and Norton B. Jamieson, Mechanical Engineering, vol. 76, May 1954, pp. 603-606. Helicopter's Hopes Lifted by Turboprops, by Robert M. Loebelson, Amer. Aviation, vol. 18, July 5, 1954, pp. 15-16. Anglo-American Jewel (Description of the Wright J-65 Sapphire), Flight, vol. 65, June 18, 1954, pp. 787-788. Turbo-Wasp Dissected (Prat t and Whitney J-57), Flight, vol. 65, May 14, 1954, pp.619-620. Compression Ignition Gas Turbine (Napier Nomad), by C. D. Carmichael, Shell Aviation News, No. 192, June 1954, pp. 16-20. Gas Turbines for Helicopters, by H, C. Maskey, Continental Aviation and Engng. Corp., Feb. 1954, 17 pp. Experiments on Model Thrust Reversers for Jet Aircraft, by M. A. Hiatt , Boeing AircraflCo. Document No. D-15077, March 1954, Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine. I. Methods for Determining Heat Transfer Characteristics, by H. H. Ellerbrock and R. R. Ziemer. I I . Methods for Determining Cooling-Air Flow Characteristics, by H. H. Ellerbrock. I I I . Methods for Determining Power and Efficiency, by H. H. Ellerbrock I I I , and R. R. Ziemer, NACA RM E50A05, and E50A06, Jan. 1950, and E50E18, May 1950. (Declassified 1953) Effect of Air Distribution on Radial Temperature Distribution in One-Sixth Sector of Annular Turbojet Combustor, by Herman Mark and Eugene V. Zettle, NACA R M E9L22, Sept. 1949. (Declassified 1953) Radiant Heat Transfer From Flames in a Singule Tubular Turbojet Combustor, by Leonard Topper, NACA R M E52F23, June 1952. (Declassified 1953) Comparison of Outside-Surface HeatTransfer Coefficients For Cascades of Turbine Blades, by James E. Hubbart, NACA R M E50C28, March 1950. (Declassified 1953) Heat Transfer and Operating Characteristics of Aluminum Forced-Convection and Stainless-Steel Natural Convection Water-Cooled Single-Stage Turbines, by John C. Freche and A. J. Diaguila, NACA R M E50DO3a, April 1950. (Declassified 1953) Analytical Investigation of Flow and Heat Transfer in Coolant Passages of Free-Convection Liquid Cooled Turbines, by E. R. G. Eckert and Thomas W. Jackson, NACA R M E50D25, April 1950. (Declassified 1953) Numerical Solution of Equations for One-Dimensional Gas Flow in Rotating Coolant Passages, by W. Byron Brown and Richard J. Rossbacb, NACA R M E50E04, May 1950. (Declassified 1953) Extension of Boundary Layer Heat Transfer Theory to Cooled Turbine Blades, by W. Byron Brown and Patrick L. Donoughe, NACA R M E50F02, June 1950. (Declassified 1953) Analytical Determination of Local Surface Heat Transfer Coefficients For Cooled Turbine Blades From Measured Metal Temperatures, by W. Byron Brown and Jack B. Esgar, NACA R M E50F09, June 1950. (Declassified 1953) Determination of Gas-to-Blade Convection Heat-Transfer Coefficients on a Forced Convection, Water Cooled Singlestage Aluminum Turbine, by John C. Freche and Eugene F . Schum, NACA R M E50J23, Oct., 1950. (Declassified 1953) Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions For Heated and Cooled Impulse Turbine Blades in Static Cascades, by James E. Hubbart and Eugene F. Schum, NACA R M E50L20, Dec. 1950. (Declassified 1953) Determination of Blade to Coolant Heat Transfer Coefficients on a Forced Convection, Water-Cooled, Single-Stage Turbine, by John C. Freche and Eugene F. Schum, NACA R M E51E18, May 1951. (Declassified 1953) Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration Cooled Walls With Application To Turbine Blade Cooling, by E. R. G. Eckert and John N. B. Livingood, NACA R M E51F22, June 1951. (Declassified 1953) Blade to Coolant Heat Transfer Results and Operating Data From a Natural Convection Water Cooled Single-Stage Turbine, by Anthony J. Diaguila and John C. Freche, NACA R M E51I17, Sept. 1951. (Declassified 1953) Experimental Investigation of CoolantFlow Characteristics of a Sintered Porous Turbine Blade, by Edward R. Bartoo, Louis J. Schafer, Jr., and Hadley T. Richards, NACA R M E51K02, Nov. 1951. (Declassified 1953) Experimental Investigation of the HeatTransfer Characteristics of an Air-Cooled Sintered Porous Turbine Blade, by Louis J. Schafer, Jr., Edward R. Bartoo, and Hadley T. Richards, NACA R M E51K08, Nov. 1951. (Declassified 1953) Pressure Drop in Coolant Passages of Two Air-Cooled Turbine Blade Configurations, by W. Byron Brown and Henry O. Slone, NACA R M E52D01, April 1952. (Declassified 1953) Comparison of Calculated and Experimental Temperatures of Water-Cooled Turbine Blades, by Eugene F . Schum, John C. Freche, and William J. Stelpflug, NACA R M E52D21, April 1952. (Declassified 1953) Analytical Investigation of Two Liquid Cooling Systems For Turbine Blades, by Thomas W. Jackson and John N. B. Livingood, NACA R M E51F04, June 1951. (Declassified 1953) Experimental Investigation of AirCooled Turbine Blades in Turbojet Engine. X-Endurance Evaluation of Several TubeFilled Rotor Blades, by Jack B. Esgar and John L. Clure, NACA R M E52B13, Feb. 1952. (Declassified 1953)
The equilibrium boundary layer flow at the stagnation point of a blunt body at very high enthalpies in air and in the simulated atmosphere of Venus (C02) has been calculated. The effects of dissociation and ionization are taken into account by means of the total thermodynamic and transport property concept. Correlation of the numerical results shows that a single simple equation will predict the stagnation point heat transfer rate at flight velocities between 6000 and 50,000 fps. Wall temperatures between 540° and 5400°R and stagnation pressures between 0.001 and 100 atm were considered. The same correlation equation is valid in Earth's atmosphere, as well as in the simulated atmosphere of Venus. The theoretical results are compared with experimental heat transfer data obtained in partially ionized air and in CO2. The agreement between theory and experiment is satisfactory. It is also shown that reasonable results for the heat transfer from an ionized boundary layer can be obtained from the results of Fay and Riddell by consistently neglecting the effects of ionization.
Indexes 1 and 2 denote the condition before and after the wave, respectively. Velocities are measured in a coordinate system connected with the wave. Ro ta ry (magnetohydrodynamic) discontinuities are also stable ( l ) . 1 When investigating plane stat ionary flows, utilization of the hodograph plane of the velocity is convenient. In Refs. 2 and 3, sets of characteristic maps have been plot ted in this plane, and in Ref. .4, shock polar diagrams for flows with parallel field and velocity vectors. The vectors plotted in Ref. 4 have been obtained from the conditions of conservation of mass, impulse, energy of the flow and entropy increase. Let us investigate which of the requirements obtained in this manner also satisfies the stability conditions [1 and 2] . Using the notat ions of Ref. 4, we may rewrite conditions [1 and 2] in the form
T PHASE method of measuring small time intervals is used directly or indirectly for investigating propagation conditions and measuring the velocity of electromagnetic waves (1,4); it is employed in radio-geodesy and radionavigation (2,3,5), in fluorimetry (6,7), in time (frequencies) (10) standards for measuring the dielectric permeability of substances (11), and in other fields of experimental physics. It is used for the radio-physical modification of SAGNAC's experiment, and it shows that the velocity of light is independent of the rate of movement of the source of radiation (8,9). Two-channel phase meters are used in these experiments where, as already known, resolution is increased by phase amplification, that is, multiplying the frequency co0 by n times (12), so that it is possible to measure smaller time intervals, since
The ultrasonic welding of metals has not been adequately investigated, and the mechanism behind formation of the bond has been given different explanations. In Refs. 1 and 2 ultrasonic welding is distinguished as a unique way of bonding metals, unlike the more familiar techniques, and yet the positive contribution of heating of the parts during welding due to friction is noted. The authors feel that the main factor causing breakdown of the continuity of the surface films and their elimination is the relative displacement of the parts and the plastic flow of the metal in the welding zone. In the opinion of the author of Ref. 3, the principal factors promoting formation of the bond are the increased atomic energy level of the crystal lattice of the metal near the welded surfaces, activation of diffusion processes in the ultrasonic field, and the appearance of considerable shear stresses at the microcontacts. The combined action of these factors causes the formation of crystals at the interface of the components. In Refs. 4 and 5 the similarity between the gripping action in ultrasonic welding and dry friction is pointed out. This postulate, however, is confirmed by calculation and experiment only for the case of contact between the tip of the ultrasonic tool and a plate. In Ref. 6 ultrasonic welding is regarded as a special case of pressure welding at high temperatures. The action of the ultrasonic oscillations amounts to removal of the surface film and heating of the contact zone to a temperature at which the resistance of the parts to deformation becomes lowered several times. Investigations conducted at the Metallurgy Institute, Academy of Sciences of the USSR, on formation of the bond in ultrasonic welding show that one important effect taking place in welding is heating of the parts at their point of contact. In the following article we present some data from a study of the distribution of the temperature field in welded parts during the process of ultrasonic welding.
This paper contains experimental data on an interesting gas mixture. Unfortunately, the authors make no attempt to interpret their experimental findings in quantitative terms. They also do not supply sufficient details concerning the experimental studies to permit quantitative interpretation by an interested reader. It is unlikely that a note of the type reviewed here would be printed in a Western journal without detailed description of the material from which the vessel was constructed and of the precise dimensions of the vessel. This information is clearly relevant, since the surface material, for vessels of presumably the same shape, does affect the observed explosion limits. In view of the long history of excellent work on explosion limits in the USSR in the tradition of the Semenoff school, it appears reasonable to regard the enclosed note as an interim report. For discussion of important studies on explosion limits and more extensive references to the literature, the references listed below may be consulted. An attempt at quantitative interpretation of explosion limits in the 03-02 system will be facilitated by reference to the following report: "Reaction Kinetics, Thermodynamics, and Transport Properties in the Ozone-Oxygen System/' by E. S. Campbell and C. Nudelman, AFOSR TN-60-502, Department of Chemistry, New York University, N. Y. (1961).
Perturbation theory is used to calculate the correlation functions for the amplitudes and phases of the field components for a wave transmitted by a randomly inhomogeneous plasma in a magnetic field. The calculations are performed for the normal waves and also for a wave of arbitrary initial plane of polarization. (auth)
