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Metallurgy Research Operation: Quarterly Progress Report, January - March 1965: Quarterly progress report on a project to test the radiation effects on metallurgy.
Metastable States of Hyperfragments and the Anomalous Magnetic Moment of the Λ-Hyperon: "We want to point out that there is a possible method for determining the anomalous magnetic moment of the Λ from the observation of metastable states of hyperframents. There are two possible sources for the apparent difference of binding energies of a hyperfragment. One of these comes from the difference of Q values due to the decay into an excited and ground states of the residual nucleus. The other possibility will arise if there exists a metastable state of the decaying hyperfragment."
Meteore 63 Commercial Seaplane: Societe Provencale de Constructions Aeronautiques, builder of the "Meteore 63" has constructed a three engine (biplane) seaplane which has met conditions for a seaworthy certificate of the first class. A description of the design, hull, tail, power plant, characteristics, performances, drawings, and photographs are provided.
Meteorological Analysis of Icing Conditions Encountered in Low-Altitude Stratiform Clouds: "Liquid-water content, droplet size, and temperature data measured during 22 flights in predominately stratiform clouds through the 1948-49 and the 1949-50 winters are presented. Several icing encounters were of greater severity than those previously measured over the same geographical area, but were within the limits of similar measurements obtained over different terrain within the United States. An analysis of meteorological conditions existing during the 74 flights conducted for four winters indicated an inverse relation of liquid-water concentration to maximum horizontal extent of icing clouds" (p. 1).
Meteorological Conditions Along Airways: This report is an attempt to show the kind of meteorological information that is needed, and is in part available, for the purpose of determining operating conditions along airways. In general, the same factors affect these operating conditions along all airways though in varying degree, depending upon their topographic, geographic, and other characteristics; but in order to bring out as clearly as possible the nature of the data available, a specific example is taken, that of the Chicago-Dallas airway on which regular flying begins this year (1926).
Meteorological Conditions Associated With Flight Measurements of Atmospheric Turbulence: "The results obtained from a series of flight measurements of atmospheric turbulence within convective-type clouds and from meteorological soundings are presented together with descriptions of the flights and concurrent weather conditions. These results are presented to provide a background of experience for the forecaster and pilot by illustrating the turbulence conditions as indicated by effective gust velocities in convective-type clouds under spring and summer weather conditions along the eastern coast of the United States" (p. 1).
Meteorological Conditions During the Formation of Ice on Aircraft: These are the results of a number of records recently secured from autographic meteorological instruments mounted on airplanes at times when ice formed. Ice is found to collect on an airplane only when the airplane is in some form of visible moisture, such as cloud, fog, mist, rain. etc., and the air temperature is within certain critical limits. Described here are the characteristics of clear ice and rime ice and the specific types of hazards they present to airplanes and lighter than air vehicles.
A meteorological measure of maximum gust velocities in clouds: Report presenting analytical considerations of the energy transformations in convective-type clouds indicate that a simple function of the height of convective activity and horizontal-temperature variations could yield a measure of the gustiness in clouds. A simplified relation that may be used to forecast the maximum effective gust velocities within convective-type clouds is developed. The analysis indicates that the method might be extended to almost all cloud types.
Meteorological-Physical Limitations of Icing in the Atmosphere: The icing hazard can, in most cases, be avoided by correct execution of the flights according to meteorological viewpoints and by meteorologically correct navigation (horizontal and, above all, vertical). The zones of icing hazard are usually narrowly confined. Their location can be ascertained with, in most cases, sufficient accuracy before take-off.
Meteorological Problems Associated With Commercial Turbojet-Aircraft Operation: Memorandum presenting an analysis and evaluation of the meteorological requirements and problems anticipated with the operation of commercial turbojet aircraft. Discussions concerning problems of temperature, wind, pressure, ceiling, visibility, cloud and clear-air turbulence, icing, and communication are included in this study.
Meteorology and Aeronautics: A handbook in which properties and general phenomena of the atmosphere which aeronauts and aviators should understand are discussed.
A Meter for Timing the Flow of Very Small Volumes of a Gas: "A flowmeter has been developed which combines a volume-time measurement of the flow, regulation of the rate, and a determination or presetting of the pressure head producing the flow. This meter is capable of accurately metering and controlling very small rates of gas flow within a closed system such as those required in a small capillary tube gas viscosimeter" (p. 1).
Metering Characteristics of Carburetors: Report presents the results of an extensive experimental investigation of the performance of different types of carburetors as effecting the maintenance under all conditions of correct ratio between the weights of fuel and air. It also gives a description of the Bureau of Standards carburetor test plant, test equipment and measuring instruments used to determine the metering characteristics of carburetors.
Methane Contents of Oil Shale from the Piceance Basin, Colorado: Report issued by the Bureau of Mines over studies conducted on oil-shale deposits of the Piceance Basin. The gas content of the deposits is discussed. This report includes maps, and illustrations.
Methane Control Research: Summary of Results, 1964-80: From Abstract: "This bulletin summarizes the work conducted under the Bureau of Mines methane control research program during the years 1964 to 1979. This bulletin provides a comprehensive source of information on the accomplishments of the Bureau's methane control research program, on the technology developed, and the direction of further research."
Method and Cost of Dredging Sand and Gravel by the Ohio River Sand Co., Louisville, Kentucky: Report issued by the U.S. Bureau of Mines discussing dredging methods of used by the Ohio River Sand Company. The different methods and costs used to recover gravel and sand are described. This report includes tables and illustrations.
Method and Cost of Mining the Thick Freeport Coal in a Second Western Pennsylvania Mine: From introduction: The purpose of this paper is to present a detailed description of the methods employed and the equipment used, with the results obtained in the operation of this mine in the thick Freeport bed on the northern end of the field, near the Alleghegny-Butler county line in western Pennsylvania. It may be classed as a captive mine, as the largest portion of the product is consumed at the by-product plants of the parent company
Method and Graphs for the Evaluation of Air-Induction Systems: Note presenting graphs for rapid evaluation of air-induction systems from considerations of their aerodynamic-performance parameters in combination with power-plant characteristics. The graphs cover the range of supersonic Mach numbers up to 3.0. The illustrative examples indicate that the inlet area required for optimum performance must change with altitude at a fixed Mach number as well as with Mach number at a fixed altitude.
Method and Graphs for the Evaluation of Air-Induction Systems: "Graphs have been developed for rapid evaluation of air-induction systems from considerations of their aerodynamic-performance parameters in combination with power-plant characteristics. The graphs cover the range of supersonic Mach numbers to 3.0. Examples are presented for an air-induction system and engine combination of two Mach numbers and two altitudes in order to illustrate the method and application of the graphs" (p. 793).
Method and Simple Apparatus for Testing Passivated Alloys: Development of a test method and apparatus for passivity of chromium alloys which eliminates the usual sources of error.
Method and tables for determining the time response to a unit impulse from frequency-response data and for determining the fourier transform of a function of time: From Summary: "A simple and rapid method is presented for the determination of the time response to a unit impulse from a frequency-response data and for evaluating the Fourier transform of a function of time. Both methods are applicable to linear functions for which Fourier transforms exist. Tables are presented which greatly reduce the time required to perform the computations. Procedures for performing the calculations by use of the tables are illustrated and outlined step by step."
Method for Analyzing Indeterminate Structures Stressed Above Proportional Limit: "An analytical method based on successive approximations is presented for determining the loads and deflections throughout an indeterminate structure in which one or more of the members have been stressed beyond their proportional limits. Theoretical analyses of three structures are compared with tests and found to agree very closely. For the sake of simplicity and clarity, only coplanar pin-ended structures have been analyzed and tested" (p. 1).
A Method for Beta-Gamma Hand and Shoe Counting Under Varying Background Conditions: Report containing a method for beta-gamma counting of hands, shoes, and clothing via an instrument that employs scintillation detectors and solid-state circuits.
Method for Calculating Effects of Dissociation on Flow Variables in the Relaxation Zone Behind Normal Shock Waves: Report presenting generalized expressions and charts which depend on the shock Mach number, initial state of the gas, and an enthalpy parameter for the temperature, pressure, density, and flow velocity behind a shock wave.
A Method for Calculating Flow Fields of Cowlings with Known Surface-Pressure Distributions: Memorandum describing a way in which the data of three previous reports can be used to compute the incompressible flow fields for cowling-spinner combinations and open-nose inlets for use in the design of propeller shanks and cuffs. The method consists of regarding the cowling surface as replaced by a ring vortex sheet whose strength at any point is equal to the local tangential velocity.
A method for calculating heat transfer in the laminar flow region of bodies: Report presenting a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited to use to the determination of heat transfer fro the forward section of such bodies when the flow is laminar.
A method for calculating heat transfer in the laminar flow region of bodies: This report has been prepared to provide a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited in use to the determination of heat transfer from the forward section of such bodies when the flow is laminar. A comparison of the calculated average heat-transfer coefficient for the nose section of the wing of a Lockheed 12-A airplane with that experimentally determined shows a satisfactory agreement. A sample calculation is appended.
Method for calculating lift distributions for unswept wings with flaps or ailerons by use of nonlinear section lift data: A method is presented which allows the use of nonlinear section lift data in the calculation of the spanwise lift distribution of unswept wings with flaps or ailerons. This method is based upon lifting line theory and is an extension to the method described in NACA rep. 865. The mathematical treatment of the discontinuity in absolute angle of attack at the end of the flap or aileron involves the use of a correction factor which accounts for the inability of a limited trigonometric series to represent adequately the spanwise lift distribution. A treatment of the apparent discontinuity in maximum section lift coefficient is also described. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of calculated characteristics with those obtained experimentally are also presented.
Method for calculating the aerodynamic loading on an oscillating finite wing in subsonic and sonic flow: Report presenting a method for determining the air forces on an oscillating finite wing of general plan form in subsonic flow, including the limiting case of sonic flow. The method is applied to rectangular and delta wings and is compared to existing theory.
Method for calculating the aerodynamic loading on an oscillating finite wing in subsonic and sonic flow: A method is presented for calculating the loading on a finite wing oscillating in subsonic or sonic flow. The method is applicable to any plan form and may be used for determining the loading on deformed wings. The procedure is approximate and requires numerical integration over the wing surface.
A method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow: From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."
A method for calculating the contour of bodies of revolution with a prescribed pressure gradient at supersonic speed with experimental verification: Report presenting a method to compute the contour of a body for a prescribed pressure distribution based on the theory of characteristics. A mode was constructed with an initial included cone angle of 30 degrees and a contour to give a linear pressure distribution for a free-stream Mach number of 3.13.
A Method for Calculating the Heat Required for the Prevention of Fog Formations on the Inside Surfaces of Single-Panel Bullet-Resisting Windshields During Diving Flight: Note presenting an investigation to provide a means for calculating the heat required for the prevention of fog formations on the inside surfaces of single-panel bullet-resisting windshields during diving flight. An analysis was made to provide relationships for the heat required considering the transient heating of the windshield during diving flight.
A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing Conditions: Report presenting an equation for calculating the heat flow required from the surface of an internally heated windshield in order to prevent ice accretions during flight in specified icing conditions. Results regarding the internally heated windshield characteristics, external discharge windshields, and prediction of heating requirements for both types of windshields are provided.
A Method for Calculating the Lift and Center of Pressure of Wing-Body-Tail Combinations at Subsonic, Transonic, and Supersonic Speeds: Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.
Method for calculating the rolling and yawing moments due to rolling for unswept wings with or without flaps or ailerons by use of nonlinear section lift data: From Summary: "The methods of NACA reports 865 and 1090 have been applied to the calculation of the rolling-moment and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods are based on lifting-line theory and allow the use of nonlinear section lift data. The method presented in this report permits calculations to be made somewhat beyond maximum lift for wings having no twist or continuous twist and employing airfoil sections which do not display large discontinuities in the lift curves. Calculations can be made up to maximum lift for wings with discontinuous twist such as that produced by partial-span flaps or ailerons, or both. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved."
A Method for Calculating the Subsonic Steady-State Loading on an Airplane With a Wing of Arbitrary Plan Form and Stiffness: Note presenting a method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers.
Method for calculating wing characteristics by lifting-line theory using nonlinear section lift data: Report presenting a method for calculating wing characteristics by lifting-line theory using nonlinear section lift data. The wing characteristics calculated from general nonlinear section lift data have been found to agree much closer with experimental data in the region of maximum lift coefficient than those calculated on the assumption of linear section lift curves.
Method for calculating wing characteristics by lifting-line theory using nonlinear section lift data: "A method is presented for calculating wing characteristics by lifting-line theory using nonlinear section lift data. Material from various sources is combined with some original work into the single complete method described. Multhopp's systems of multipliers are employed to obtain the induced angle of attack directly from the spanwise lift distribution. Equations are developed for obtaining these multipliers for any even number of spanwise stations, and values are tabulated for 10 stations along the semispan for asymmetrical, symmetrical, and antisymmetrical lift distributions" (p. 1).
Method for Calculation of Compressible Laminar Boundary-Layer Characteristics in Axial Pressure Gradient With Zero Heat Transfer: Note presenting an extension of the Kármán-Pohlhausen method to sixth-degree velocity profiles for determining the characteristics of the compressible laminar boundary layer over an adiabatic wall in the presence of an axial pressure gradient.
Method for calculation of compressible laminar boundary layer with axial pressure gradient and heat transfer: Report presenting a rapid and sufficiently accurate method of determining laminar-boundary-layer characteristics in flow with a given free-stream Mach number and given velocity distribution at the edge of the boundary layer. The method can be easily applied to flow with zero pressure gradient for any constant Prandtl number of the order of unity and any given temperature distribution along wall.
A method for calculation of free-space sound pressures near a propeller in flight including considerations of the chordwise blade loading: This report presents tabulated values of certain definite integral that are involved in the calculation of near-field propeller noise when the chordwise forces are assumed to be either uniform or of a Dirac delta type. The tabulations are over a wide range of operating conditions and are useful for estimating propeller noise when either the concept of an effective radius or radial distributions of forces are considered. Use of the tabulations is illustrated by several examples of calculated results for some specific propellers.
Method for calculation of heat transfer in laminar region of air flow around cylinders of arbitrary cross section (including large temperature differences and transpiration cooling): Report presenting a method permitting the calculation of local heat transfer around the periphery of cylinders of arbitrary cross section in the laminar region for flow of a fluid with constant property values with an accuracy sufficient for engineering purposes. The method is applied to circular and elliptic cylinders are the results are described.
A method for calculation of hydrodynamic lift for submerged and planing rectangular lifting surfaces: A method is presented for the calculation of lift coefficients for rectangular lifting surfaces of aspect ratios from 0.125 to 10 operating at finite depths beneath the water surface, including the zero depth or planing condition. Theoretical values are compared with experimental values obtained at various depths of submergence with lifting surfaces of aspect ratios from 0.125 to 10. The method can also be applied to hydrofoils with dihedral. Lift coefficients computed by this method are in good agreement with existing experimental data for aspect ratios from 0.125 to 10 and dihedral angles up to 10 degrees.
Method for Calculation of Laminar Heat Transfer in Air Flow Around Cylinders of Arbitrary Cross Section (Including Large Temperature Differences and Transpiration Cooling): "The solution of heat-transfer problems has become vital for many aeronautical applications. The shapes of objects to be cooled can often be approximated by cylinders of various cross sections with flow normal to the axis as, for instance heat transfer on gas-turbine blades and on air foils heated for deicing purposes. A laminar region always exists near the stagnation point of such objects. A method previously presented by E. R. G. Eckert permits the calculation of local heat transfer around the periphery of cylinders of arbitrary cross section in the laminar region for flow of a fluid with constant property values with an accuracy sufficient for engineering purposes" (p. 223).
Method for Calculation of Pressure Distributions on Thin Conical Bodies of Arbitrary Cross Section in Supersonic Stream: Note presenting an approximate method for calculating the pressure distribution on conical bodies of noncircular cross section in a supersonic flow field. By a superposition of elementary conical flows due to line sources, the flow about an arbitrary cone may be described.
Method for calculation of ram-jet performance: Report presenting a method utilizing precalculated solutions graphically presented for calculating subsonic or supersonic ramjet performance parameters with the associated equations and graphs. By assuming constant values of specific-heat ratio and gas constant equal to those of standard air, the thrust-coefficient calculation has been reduced to a few simple operations.
Method for Comparing Small AC Voltages in the Presence of Large DC Components: A feedback technique has been developed to equalize the DC levels of two signal sources so that AC signal components which are much smaller than the DC levels can be compared accurately without introducing a low frequency cut-off and consequent rate-dependency into the system. A digital integrator in the feedback loop provides a highly stable long-term "memory" so that the correct level will be maintained during intervals when the signals are "frozen" at some arbitrary point.
A method for computing leading-edge loads: From Summary: "In this report a formula is developed that enables the determination of the proper design load for the portion of the wing forward of the front spar. The formula is inherently rational in concept, as it takes into account the most important variables that affect the leading-edge load, although theoretical rigor has been sacrificed for simplicity and ease of application. Some empirical corrections, based on pressure distribution measurements on the PW-9 and M-3 airplanes have been introduced to provide properly for biplanes. Results from the formula check experimental values in a variety of cases with good accuracy in the critical loading conditions. The use of the method for design purposes is therefore felt to be justified and is recommended."
A Method for Constructing the Complete HIFAR Neutron Spectrum from the Available Spectral Indices: A method is given for constructing the complete neutron spectrum for a well-moderated thermal reactor such a HIFAR, from the total effective flux, the temperature of the Maxwellian, the epithermal spectral index and the total integrated fission flux. A sample calculation is also included.

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