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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Collection: Technical Report Archive and Image Library
An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2
No Description digital.library.unt.edu/ark:/67531/metadc58368/
Ability of pilots to control simulated short-period yawing oscillations
No Description digital.library.unt.edu/ark:/67531/metadc58499/
Abnormal grain growth in M-252 and S-816 alloys
An experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth. digital.library.unt.edu/ark:/67531/metadc57131/
Abnormal grain growth in nickel-base heat-resistant alloys
No Description digital.library.unt.edu/ark:/67531/metadc57096/
Abnormal grain growth in S-816 alloy
No Description digital.library.unt.edu/ark:/67531/metadc57000/
Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes
No Description digital.library.unt.edu/ark:/67531/metadc60813/
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed
No Description digital.library.unt.edu/ark:/67531/metadc59611/
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics I : effect of air bleed at compressor outlet
An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area. A relatively simple two-step area bleed gives only a small increase in acceleration time over a corresponding variable-area bleed. For the modes of operation considered, over 84 percent of the total acceleration time was required to accelerate through the low-speed range ; therefore, better low-speed compressor performance (higher pressure ratios and efficiencies) would give a significant reduction in acceleration time. digital.library.unt.edu/ark:/67531/metadc59518/
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics III : effect of turbine stator adjustment
No Description digital.library.unt.edu/ark:/67531/metadc60396/
An acceleration schedule control for accelerating a turbojet engine and its use with a speed control
No Description digital.library.unt.edu/ark:/67531/metadc63981/
An acceleration schedule control for accelerating a turbojet engine and its use with a speed control
Accelerating-limiting controls for turbojet engines. digital.library.unt.edu/ark:/67531/metadc52973/
Accelerations and passenger harness loads measured in full-scale light-airplane crashes
No Description digital.library.unt.edu/ark:/67531/metadc56800/
Accelerations in fighter-airplane crashes
No Description digital.library.unt.edu/ark:/67531/metadc63594/
Accelerations in transport-airplane crashes
No Description digital.library.unt.edu/ark:/67531/metadc56808/
Accepted Limit Values of Air Pollutants
Report issued by the U.S. Bureau of Mines discussing, as stated in the introduction, the "accepted maximum permissible concentrations of air pollutants from the standpoints of health, damage to vegetation, damage to property, and requirements of industrial processes" (p. 1). This report includes tables. digital.library.unt.edu/ark:/67531/metadc67065/
Accidents from explosives at metal and nonmetallic mines
Circular produced by the U.S. Bureau of Mines to promote safety through a series of reports on accident prevention in mines. According the the scope statement, "This is the fourth section of the revised series of circulars that cover various phases of accident prevention in metal and nonmetallic mines; it give information on accidents and injuries from storing, handling, and using explosive in metal and nonmetallic mines and discusses the precautions by which they can be prevented" (p. 2). digital.library.unt.edu/ark:/67531/metadc40319/
Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow
No Description digital.library.unt.edu/ark:/67531/metadc56461/
The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams
No Description digital.library.unt.edu/ark:/67531/metadc57907/
An accurate and rapid method for the design of supersonic nozzles
No Description digital.library.unt.edu/ark:/67531/metadc57389/
Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles
No Description digital.library.unt.edu/ark:/67531/metadc56184/
Acid-Mine-Drainage Problems: Anthracite Region of Pennsylvania
Report from the U.S. Bureau of Mines discussing the anthracite region of Pennsylvania and the efforts to prevent coal-mine drainage into nearby streams. According to the introduction, "The purpose of this report is not to develop a practicable or feasible method or process of treating acid mine water but rather to present available factual and deduced data that may be useful in showing pH range over which the treatment is to take place and the sludge products most likely to be handled" (p. 2). digital.library.unt.edu/ark:/67531/metadc12667/
Acoustic analysis of ram-jet buzz
No Description digital.library.unt.edu/ark:/67531/metadc57885/
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces
No Description digital.library.unt.edu/ark:/67531/metadc57843/
Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines
No Description digital.library.unt.edu/ark:/67531/metadc57452/
Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel
No Description digital.library.unt.edu/ark:/67531/metadc56258/
Acoustics of a nonhomogeneous moving medium.
Theoretical basis of the acoustics of a moving nonhomogeneous medium is considered in this report. Experiments that illustrate or confirm some of the theoretical explanation or derivation of these acoustics are also included. digital.library.unt.edu/ark:/67531/metadc65701/
An active particle diffusion theory of flame quenching for laminar flames / Dorothy M. Simon and Frank E. Belles
An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be consistent with the mechanism. The derived equation is used with the lean inflammability limit and a rate constant calculated from burning velocity data to estimate quenching distances for propane-air (hydrocarbon lean) flames satisfactorily. digital.library.unt.edu/ark:/67531/metadc59077/
Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds
A cascade impactor, an instrument for obtaining: the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor. The droplets that enter the impactor impinge on four slides coated with magnesium oxide. Each slide catches a different size range. The relation between the size of droplet impressions and the droplet size was evaluated so that the droplet-size distributions may be found from these slides. The magnesium oxide coating provides a permanent record. of the droplet impression that is not affected by droplet evaporation after the. droplets have impinged. digital.library.unt.edu/ark:/67531/metadc53539/
Adaptation of Combustion Principles to Aircraft Propulsion, Volume 2, Combustion in Air-Breathing Jet Engines
This volume continues the NACA study of combustion principles for aircraft propulsion. The various aspects of combustion pertinent to jet engines are organized and interpreted with quite extensive information, particularly for basic or fundamental. subject matter. The report concerns only air-breathing engines and hydrocarbon fuels, and not rocket engines and high-energy fuels. Since the references have been selected to illustrate important points, the bibliographies, while thorough, are not complete. This volumes describes the observed performance and design problems of engine combustors of the principal types. These include combustor-inlet conditions; starting, acceleration, combustion limits, combustion efficiency, coke deposits, and smoke formation in turbojets; ram-jet performance; and afterburner performance and design. digital.library.unt.edu/ark:/67531/metadc63711/
Adaptation of Combustion Principles to Aircraft Propulsion, Volume I, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air
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 observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined. digital.library.unt.edu/ark:/67531/metadc61037/
Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations
No Description digital.library.unt.edu/ark:/67531/metadc61416/
Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design
No Description digital.library.unt.edu/ark:/67531/metadc60906/
Additional experiments with flat-top wing- body combinations at high supersonic speeds
Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft. digital.library.unt.edu/ark:/67531/metadc53065/
Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy
No Description digital.library.unt.edu/ark:/67531/metadc59956/
Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length
No Description digital.library.unt.edu/ark:/67531/metadc63845/
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
No Description digital.library.unt.edu/ark:/67531/metadc62574/
Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds
Additional results on the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane were obtained in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.92. The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. The sideslip-angle range investigated was from -4 degrees to 12 degrees. The investigation included effects of various arrangements of wing fences, leading-edge chord-extensions, and leading-edge notches. Various fuselage fences, spoilers, and a dive brake also were investigated. From overall considerations of lift, drag, and pitching moments, it appears that there were two modifications somewhat superior to any of the others investigated: One was a configuration that employed a full-chord fence and a partial-chord fence located at 0.63 semispan and 0.55 semispan, respectively. The second was a leading-edge chord-extension that extended from 0.68 semispan to 0.85 semispan in combination with a leading-edge notch located at 0.68 semispan. With plus or minus 10 degrees aileron, the estimated wing-tip helix angle was reduced from 0.125 at a Mach number of 0.50 to 0.088 at a Mach number of 0.92, with corresponding rates of roll of 4.0 and 5.2 radians per second. The upper aft fuselage dive brake, when deflected 30 degrees and 60 degrees, reduced the rudder effectiveness about 10 to 20 percent and about 35 to 50 percent, respectively. digital.library.unt.edu/ark:/67531/metadc65304/
Additional static and fatigue tests of high-strength aluminum-alloy bolted joints
No Description digital.library.unt.edu/ark:/67531/metadc57279/
Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques
No Description digital.library.unt.edu/ark:/67531/metadc58981/
The adhesion of molten boron oxide to various materials
No Description digital.library.unt.edu/ark:/67531/metadc64004/
Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades
The adhesive and protective characteristics of National Bureau of Standards Coating A-417 were investigated, as well as the effect of the coating on the life of forged Refractaloy 26 and cast Stellite 21 turbine blades. Coated and uncoated blades were run in a full-scale J33-9 engine and were subjected to simulated service operations consisting of consecutive 20-minute cycles (15 min at rated speed and approximately 5 min at idle). The ceramic coating adhered well to Refractaloy 26 and Stellite 21 turbine blades operated at 1500 degrees F. The coating also prevented corrosion of the Refractaloy 26, a corrosion-sensitive nickel-base alloy, and of the Stellite 21, a relatively corrosion-resistant cobalt-base alloy. Although the coating prevented corrosion of both alloys, it had no apparent effect on blade life. digital.library.unt.edu/ark:/67531/metadc59641/
Advanced Designs of Magnetic Jack-Type Control Rod Drive
Report containing information regarding magnetic jacks, which are devices used "for positioning the control rods in a nuclear reactor, especially in a reactor containing water under pressure" (page 9). Contains a description of the device, its use, test results, and illustrations. digital.library.unt.edu/ark:/67531/metadc11533/
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight
No Description digital.library.unt.edu/ark:/67531/metadc62900/
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing
No Description digital.library.unt.edu/ark:/67531/metadc63527/
Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201
No Description digital.library.unt.edu/ark:/67531/metadc62388/
Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations
No Description digital.library.unt.edu/ark:/67531/metadc64014/
Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method
No Description digital.library.unt.edu/ark:/67531/metadc58563/
The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow
No Description digital.library.unt.edu/ark:/67531/metadc55838/
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds
A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented. digital.library.unt.edu/ark:/67531/metadc56243/
Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps
No Description digital.library.unt.edu/ark:/67531/metadc61390/
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