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  • General Chemistry  (1,165)
  • THERMODYNAMICS AND COMBUSTION  (344)
  • Cell & Developmental Biology
  • 1980-1984
  • 1970-1974  (1,698)
  • 1971  (1,698)
Collection
Keywords
Publisher
Years
  • 1980-1984
  • 1970-1974  (1,698)
Year
  • 1
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    Manufacturing developments in insulation application (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Manufacturing development studies have been conducted to provide information on the fabrication and handling characteristics of a number of candidate multilayer insulation systems. The application of these complex, lightweight insulation systems to large-scale, flight-type cryogenic tankage and other structures has of necessity required the development of new methods, processes, and tooling concepts. Results of some of the studies that have contributed to the advancement of cryogenic technology are presented. The insulation systems that are of primary importance for future application are those using the sliced foam spacers, the net type spacers, the glass fiber paper spacers, and the Superfloc system which consists of tufts of dacron fibers flocked on the surface of the radiation shields.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 73-92
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  • 2
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    Design for advanced insulation systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The design of principal multilayer insulation (MLI) systems being investigated by Marshall Space Flight Center and its contractors for application to flight-type cryogenic tankage for long-term storage in space vehicles is described. The MLI systems were designed for application to a 105 in. diameter cryogenic test tank to simulate full-scale design and installation methods representative of flight-type hardware. The MLI systems selected for design represent systems suitable for use on space vehicles such as the modular nuclear vehicles that require application of thicknesses up to 6 in. The MLI systems are lightweight and structurally efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 53-72
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  • 3
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    Multilayer high performance insulation materials (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A number of tests are required to evaluate both multilayer high performance insulation samples and the materials that comprise them. Some of the techniques and tests being employed for these evaluations and some of the results obtained from thermal conductivity tests, outgassing studies, effect of pressure on layer density tests, hypervelocity impact tests, and a multilayer high performance insulation ambient storage program at the Kennedy Space Center are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. At MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 93-98
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  • 4
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    Fire extinguishment in hypobaric and hyperbaric environments (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Work that has been performed to provide information on the effects of various fire extinguishing agents in special atmospheres is discussed. Data used in the development of both equipment and techniques for manned spacecraft and related equipment are discussed. The equipment includes a hypobaric chamber suitable for low pressure use and a hyperbaric chamber for high pressure operation. The effectiveness of agents in weightless environment is also discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 163-169
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  • 5
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    The combustion process (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The effect of thermodynamic, chemical, and physical properties on the combustion of materials is discussed. The mechanisms which produce and support combustion of various materials are examined. The effects of free radical reactions, convection and gravitational effects on combustion rates, and changes in flame propagation due to size and shape of surfaces are described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 3-7
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  • 6
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    Conditions for local thermodynamic equilibrium in uranium (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Model for calculation of parameters for local thermodynamic equilibrium in uranium
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: FLORIDA UNIV. RES. ON URANIUM PLASMAS AND THEIR TECHNOL. APPL. 1971; P 173-178
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  • 7
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    Multilayer insulation thermal protection systems technology (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A summary is presented of the work performed by Marshall Space Flight Center (MSFC) and industry toward the development of flight-type multilayer insulation(MLI) systems. The MSFC MLI program is divided into three large categories: (1) the generation and compilation of MLI composite test data; (2) the analysis, design, and testing of heat flow through MLI applied to ducting, seams, electrical feedthroughs, structural supports, and the tank sidewall; and (3) the development, modification, and utilization of new testing procedures, tanks, and the test facilities. Numerous data have been generated, analyzed, and documented on different MLI composites.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Achievements Rev., Vol.4, No. 2; p 5-52
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  • 8
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    Development of materials screening tests for oxygen-enriched environments (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The criteria governing materials to be used in an oxygen enriched atmosphere and tests to determine suitability for fireproof considerations in spacecraft design are discussed. The nine tests applied to materials before acceptance in spacecraft construction are presented. The application of the standard tests to determine ranking of materials is included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 23-27
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  • 9
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    Materials for foam type insulation (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An internal foam fabrication is one of the concepts being considered for cryogenic insulation on the hydrogen tanks of the shuttle vehicle. The three-dimensional polyurethane used on the S-4 B tanks failed to meet the higher temperature requirements of the shuttle vehicle, however, and other foams under consideration include polyisocyanurates, polyphenylene oxides, polyimides, and polybenzimidazoles. Improved adhesive systems for attaching the foams to the interior tank wall are under study.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 179-184
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  • 10
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    Flammability tests for Apollo command module and lunar module mockup (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The flammability test program for Apollo command module and lunar module mockups is described. The fire safety design of the modules was verified by performing deliberate ignitions at many locations while the interior atmosphere was controlled to simulate realistic flight conditions. The data obtained for each test and restrictions on various materials are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 43-54
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  • 11
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    Manned spacecraft nonmetallic-materials flammability selection criteria and requirements (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The criteria and requirements governing the selection and use of nonmetallic materials in manned spacecraft to control potential fire hazards are reviewed. The development of flammability requirements is discussed and traced through the historical evolution. Events that dictated the changes that have taken place are discussed. The current nonmetallic material requirements are presented. Significant features of a nonmetallic materials handbook are included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 9-21
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  • 12
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    Roughness effects on heat transfer in the supersonic region of a conical nozzle (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Conical nozzle roughness on heat transfer in supersonic region
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; 394-398. (
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  • 13
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    Thermal-mechanical response of nearly opaque materials exposed to continuous radiation (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Thermal stress distribution and temperature profiles in nearly opaque spherical shell under radiant and convective heating flux
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; - ASTRONOMY 1969- TE
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  • 14
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    Experimental burning rates of single laser- ignited beryllium droplets (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Burning rates of single laser ignited beryllium droplets, considering particle size effect
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; TROPHYSICAL JOURNAL
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  • 15
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    Absorption of infrared radiation by high- density oxygen (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: IR radiation role in limiting central heater maximum temperature and heat transfer to high density oxygen in cryogenic storage systems
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; ADEMIE DES SCIENCES
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  • 16
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    Application of singular eigenfunction expansions to the propagation of periodic disturbances in a radiating grey gas (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Periodic disturbances propagation in radiating gray gas, using singular eigenfunction expansions
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; ADEMIE DES SCIENCES
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  • 17
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    An exact solution of linearized flow of an emitting, absorbing and scattering grey gas (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Emitting, absorbing and scattering gray gas flow through plane stationary normal shock wave, presenting governing equations linearized analysis
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; 9-12, 15 (
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  • 18
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    Amplification by wave distortion in unstable combustors (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Pressure wave distortion effects on combustor acoustic mode instability based on model with burning rate related to Reynolds number
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; VUE SCIENTIFIQUE ET
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  • 19
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    Flame spread over fuel beds - Solid phase energy considerations, part 2 (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Flame spread over surface of solid-fuel bed in oxygen-inert environment
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: THE INVEST. OF FLAME SPREADING OVER THE SURFACE OF IGNITING SOLID PROPELLANTS 31 MAR. 1971 (SEE N71-31426 18-33)
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  • 20
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    Lee side heating investigations. Part 2 - Lee side heating investigations of simple body like configurations (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Leeside aerodynamic heating of lifting reentry vehicle configurations
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA, WASHINGTON NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 289-309
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  • 21
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    Film stability in a vertical rotating tube with a core-gas flow. (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The linear hydrodynamic stability of a thin-liquid layer flowing along the inside wall of a vertical tube rotating about its axis in the presence of a core-gas flow is examined. The stability problem is formulated under the conditions that the liquid film is thin, the density and viscosity ratios of gas to liquid are small and the relative (axial) pressure gradient in the gas is of the same order as gravity. The resulting eigenvalue problem is first solved by a perturbation method appropriate to axisymmetric long-wave disturbances. The damped nature (to within the thin-film and other approximations made) of the nonaxisymmetric and short-wave disturbances is noted. In view of the limitations on a truncated perturbation solution when the disturbance wavenumber is not small, an initial value method using digital computer is presented. Stability characteristics of neutral, growing, and damped modes are presented showing the influences of rotation, surface tension, and the core-gas flow. Energy balance in a neutral mode is also illustrated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 14; Nov. 197
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  • 22
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    Effect of angle of attack on boundary-layer transition at Mach 21 (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Slender cone boundary layer transition under angle of attack at Mach 21 with promoted leeward and fixed windward ray
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
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  • 23
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    An evaluation of theories for predicting turbulent skin friction and heat transfer on flat plates at supersonic and hypersonic Mach numbers (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Turbulent skin friction and heat transfer prediction on flat plates and wind tunnel walls at supersonic and hypersonic Mach numbers, using Van Driest theory
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
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  • 24
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    Laminar boundary layers with large wall heating and flow acceleration (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Laminar boundary layers with large wall heating and flow acceleration, considering heat transfer parameter increase
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; TROPHYSICAL JOURNAL
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  • 25
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    Flightworthy, high performance insulation development. I (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Multilayer insulation systems for cryogenics protection aboard spacecraft, considering mechanical properties, radiation shielding, component evacuation rate and outgassing
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
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  • 26
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    Flame spreading over the surface of igniting solid rocket propellants and propellant ingredients, part 4 (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Flame spreading over surface of igniting solid rocket propellants at different pressures, and oxygen-nitrogen mixtures
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: THE INVEST. OF FLAME SPREADING OVER THE SURFACE OF IGNITING SOLID PROPELLANTS 31 MAR. 1971 (SEE N71-31426 18-33)
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  • 27
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    The mechanism of flame spreading over the surface of igniting, condensed phase materials, part 3 (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Mechanism by which flame spreads over surface of condensed-phase material in quiescent gaseous environment
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: THE INVEST. OF FLAME SPREADING OVER THE SURFACE OF IGNITING SOLID PROPELLANTS 31 MAR. 1971 (SEE N71-31426 18-33)
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  • 28
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    An investigation of the flame spreading characteristics of the ICRPG standard reference composite propellant and its constituents, part 1 (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Surface flame spreading characteristics of ICRPG reference composite propellant composed of ammonium perchlorate with polyurethane binder
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: THE INVEST. OF FLAME SPREADING OVER THE SURFACE OF IGNITING SOLID PROPELLANTS 31 MAR. 1971 (SEE N71-31426 18-33)
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  • 29
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    Spectral measurements of nitrogen continuum radiation behind incident shocks at speeds up to 13 km/sec (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Spectral measurements of nitrogen continuum radiation behind incident shocks at high speeds, suggesting free bound neutral atom-electron interactions origin
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; HYSICAL PROCESSES IN
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  • 30
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    Flightworthy, high performance insulation development. II (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Multilayer insulation systems development and selection for cryogenics thermal protection on space vehicles, considering mechanical properties, radiation shielding, components, evacuation rate and outgassing
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; DIOTEKHNIKA (
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  • 31
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    Nonisotropic exchange coefficients in turbulent swirling flames from mean value distributions (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Turbulent swirling flames nonisotropic exchange coefficients determination from time mean velocity, pressure, temperature and concentration distributions
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; - DISCRETE CONTROL S
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  • 32
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    Shape evolution of a subliming surface subjected to unsteady spatially nonuniform heat flux (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Two dimensional unsteady heat conduction in solid with subliming surface, replacing original boundary value problem by ordinary integrodifferential equation
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; - CALCULATION OF THR
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  • 33
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    The effect of high-frequency periodic disturbances on axisymmetric wake diffusion flames (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Axisymmetric wake diffusion flame response to HF periodic velocity oscillations at combustor boundaries
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; BROTECHNIKA, NO. 1(
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  • 34
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    A comparison of analysis and experiment for solid propellant combustion instability (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Combustion instability data with same solid propellants by T-burner and L super asterisk burner, discussing theoretical models of transient combustion
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; BROTECHNIKA, NO. 2(
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  • 35
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    Lee side heating investigations. Part 1 - Experimental lee side heating studies on a delta wing orbiter (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Lee surface flow and aerodynamic heating on delta wing orbiter
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 267-287
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  • 36
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    Summary of the NASA-SRI Round Robin Ablation Program (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: NASA-SRI Round Robin Ablation Program summary, discussing dimensional analysis, Teflon, nylon and surface temperature
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; 121- 147. (
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  • 37
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    Influence of water vapor upon the properties of shocked air in thermodynamic equilibrium (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Water vapor effects on shock compressed air in thermodynamic equilibrium by computer program, noting temperature and electron concentration reduction
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; IBRATIONAL COMBUSTIO
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  • 38
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    The effect of boundaries on the velocity deficit and the limit of gaseous detonations (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Boundary effects on gaseous detonation velocity deficit and limit using approximation into boundary layer equations, comparing to experimental data
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; UG REVUE(
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  • 39
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    Influence of differences in thermochemistry data upon high-temperature gas composition (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Thermochemistry data changes influence in form of heat of formation, partition functions, specie free energy or specific heat on high temperature gas mixtures composition
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; - DISCRETE CONTROL S
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  • 40
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    Thermal emissivity and solar absorptivity of aluminum coated with double layers of aluminum oxide and silicon oxide (1971)
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    Publication Date: 2011-08-16
    Description: Thermal emissivity and solar absorptivity of Al coated with surface layers of aluminum oxide and silicon oxide, describing fabrication techniques and performance measurements
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; TROPHYSICAL JOURNAL
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  • 41
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    A method of treating the nongray error in total emittance measurements (1971)
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    Publication Date: 2011-08-16
    Description: Total emittance measurements by portable IR reflectometer, tabulating nongray error effects
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; SEARCH(
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  • 42
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    Ablation and luminosity of artificial meteors (1971)
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    Publication Date: 2011-08-16
    Description: Artificial meteors ablation and luminosity measurements, using ballistic range shadowgraph and radiometric equipment for velocity history, shock wave formation and mass loss process
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
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  • 43
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    Development status of reusable nonmetallic thermal protection (1971)
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    Publication Date: 2011-08-16
    Description: Development of reusable oxidation resistant carbon-carbon laminates and surface insulation materials for thermal protection systems
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 2 APR. 1971; P 1-38
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  • 44
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    Plume impingement during separation of a two stage space shuttle vehicle (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Optimum separation trajectory analysis for two stage space shuttle configuration considering plume impingement effect
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 393-421
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  • 45
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    Shock interference heating on the space shuttle booster during ascent (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Aerothermodynamic shock heating of space shuttle booster surface during atmospheric ascent
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA, WASHINGTON NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 245-266
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  • 46
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    Shock interference heating and density-ratio effects. Part 1 - Flow field visualization, thermocouple measurements, and analysis (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Flow visualization, thermocouple measurements, and analyses of shock interference heating effects on straight wing space shuttle model
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 185-215
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  • 47
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    An analysis of predicted space shuttle temperatures and their impact on thermal protection systems (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Comparison of space shuttle aerodynamic heating analyses for metallic heat shield and surface insulation concepts
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA, WASHINGTON NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 75-96
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  • 48
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    Shock interference heating and density ratio effects. Part 2 - Hypersonic density ratio effects (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Hypersonic shock/density ratio effects in aerothermodynamic heating of space shuttle configuration
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 217-243
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  • 49
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    Analysis of the longitudinal high frequency stability of a staged combustion cycle, Appendix B (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Time lag theory for longitudinal high frequency stability analysis on staged combustion cycle of liquid propellant rocket engine
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: STABILITY CHARACTERIZATION OF ADVANCED INJECTORS, DESIGN GUIDE, VOL. 2 FEB. 1971 (SEE N71-20415 09-28)
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  • 50
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    Thermodynamic properties and nozzle flow of hydrogen to 1000 atm and 100,000 K (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Thermodynamic properties and nozzle flow calculations for high temperature and pressure hydrogen, presenting results in Mollier diagram
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; ADEMIE DES SCIENCES
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  • 51
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    Kinetic limitations on the diffusional control theory of the ablation rate of carbon. (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: It is shown that the theoretical maximum oxidation rate is limited in many cases even at temperatures much higher than 1650 deg K, not by oxygen transport, but by the kinetics of the carbon-oxygen reaction itself. Mass-loss rates have been calculated at air pressures of 0.01 atm, 1 atm, and 100 atm. It is found that at high temperatures the rate of the oxidation reaction is much slower than has generally been assumed on the basis of a simple linear extrapolation of Scala's 'fast' and 'slow' rate expressions. Accordingly it cannot be assumed that a transport limitation inevitably must be reached at high temperatures.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 8; Dec. 197
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  • 52
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    Thin wing corrections for phase-change heat-transfer data. (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Since no methods are available for determining the magnitude of the errors incurred when the semiinfinite slab assumption is violated, a computer program was developed to calculate the heat-transfer coefficients to both sides of a finite, one-dimensional slab subject to the boundary conditions ascribed to the phase-change coating technique. The results have been correlated in the form of correction factors to the semiinfinite slab solutions in terms of parameters normally used with the technique.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 8; Dec. 197
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  • 53
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    Criteria for electrically heated temperature probes in flames. (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Measurement techniques proposed by Gilbert and Lobdell (1953) and Rein and O'Laughlin (1967) are considered, giving attention to an apparent paradox. The criteria under which the assumptions made for the measurement techniques apply are specified. If sensors of different diameters are tested and the resultant plots of the parameter ?S' vs the wire temperature intersect below the abscissa, the considered measurement techniques are not applicable.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 10; Jan. 197
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  • 54
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    New half-range differential approximation for spherically-symmetric radiative transfer. (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A new half-range differential approximation for radiative transfer with spherical symmetry is presented. The development is motivated by the various failures of existing differential approximations in determining emissive-power distributions and heat transfer for concentric-spheres problems. The new approach represents a modification of the four-moment double spherical-harmonics method, to which it reduces in the planar limit. The difference is effected by relocating the discontinuity of the assumed directional distribution of radiation intensity. The shift takes the discontinuity from precisely on the division between radially inward and radially outward, to just within the radially-outward directional half range. The method is tested on a variety of concentric spheres problems with and without internal heat sources, reproducing all the important features of the exact results.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 9; Dec. 197
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  • 55
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    Analysis of heat transfer for compressible flow in two-dimensional porous media (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Compressible gas flow in two dimensional porous wall, calculating heat transfer and mass flow by conformal mapping for Laplace equation solution
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; - PHYSICAL AND RADIO
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  • 56
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    Flammability testing conducted in support of Apollo 13 (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In support of the Apollo 13 investigation of the oxygen tank failure, flame propagation rates were determined for Teflon insulation in cryogenic and ambient temperature oxygen for upward, downward, and zero g burns. The propagation rates depended heavily on configuration and varied from 4.8 to 10.9 cm/sec for upward one g burns to 0.48 cm/sec for zero g burns. In addition to the flame propagation rates, tests were conducted to determine if Teflon burning in cryogenic oxygen could ignite metals (promoted ignition) with which it came in contact. Tests conducted on various metal alloys used in the oxygen tank indicated that most of the alloys could be ignited by burning Teflon in certain configurations. After the propagation rates and promoted metal ignitions had been evaluated, a test was conducted on a quantity gauge and wire harness used in the oxygen tank to determine if flame propagation to the tank wall was possible. Propagation of the wire bundle after ignition resulted in a catastrophic failure of the test vessel in the area of the quantity gauge.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: MSC Cryog. Symp. Papers; p 455-474
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  • 57
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    Zero-gravity transient thermal mixing simulation (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The experimental program described is an outgrowth of independent investigations into alternate redesign concepts for the Apollo SM cryogenic oxygen storage system. The experiments were continued, after the redesign was established, to provide physical insight into transient thermal mixing in zero-gravity and to aid in the characterization of the system performance in flight. Zero-gravity heat transfer and fluid mixing were simulated experimentally through an analogy between unsteady heat conduction and species diffusion. To further support numerical analyses of the cryogenic oxygen storage system, the experimental investigation was extended to include a cubical tank geometry, representative of existing numerical models. In general, the transient flow patterns in the cubical tank are far more complex than those of the spherical tank and the extent of fluid mixing is significantly greater but less repeatable.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: MSC Cryog. Symp. Papers; p 407-432
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  • 58
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    Correlation of Apollo oxygen tank thermodynamic performance predictions (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Parameters necessary to analyze the stratified performance of the Apollo oxygen tanks include g levels, tank elasticity, flow rates and pressurized volumes. Methods for estimating g levels and flow rates from flight plans prior to flight, and from quidance and system data for use in the post flight analysis are described. Equilibrium thermodynamic equations are developed for the effects of tank elasticity and pressurized volumes on the tank pressure response and their relative magnitudes are discussed. Correlations of tank pressures and heater temperatures from flight data with the results of a stratification model are shown. Heater temperatures were also estimated with empirical heat transfer agreement with flight data when fluid properties were averaged rather than evaluated at the mean film temperature.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Manned Spacecraft Center MSCCryog. Symp. Papers; p 103-129
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  • 59
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    Utilization of available skills and materials in fire prevention (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Procedures for installing fire protection systems in large buildings are discussed. Factors considered in the safety management are: (1) distribution of water supply, (2) design and location of exits, (3) emergency power system, and (4) maintenance procedures.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Univ. of S. Calif. Fireproofing and Safety Symp. Proc.; p 33-40
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  • 60
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    How to reduce your fire insurance rates (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Construction procedures and utilization of materials to reduce the cost of insuring large buildings against losses from fire are discussed. Examples of good and bad techniques in building construction and fire safety management are provided. The inadequacies of building codes and the hazards resulting from improper construction are examined.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Univ. of S. Calif. Fireproofing and Safety Symp. Proc.; p 41-53
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  • 61
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    Introduction to program subject: Fireproofing (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various processes for fireproofing materials are discussed. The conditions under which fireproofing measures may be adequate are compared with conditions under which the measures may be inadequate. The mechanisms for flame propagation and conditions required for ignition and burning are described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Fireproofing and Safety Symp. Proc.; p 19-32
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  • 62
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    The Flash Evaporator for Transient Heat Loads (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Liquid spray flash evaporator for space shuttle thermal control
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Kennedy Space Center Space Shuttle Technol. Conf., Vol. 2; p 35-65
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  • 63
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    The effects of gravity on flammability (1971)
    In:  CASI
    Details
    Publication Date: 2017-01-27
    Description: The effects of weightlessness and increased gravity on flammability and flame propagation are discussed. The test equipment and procedures for determining gravity effects are described. Comparisons are made between flammability under normal gravity conditions and occurrences under altered gravity conditions
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; 137-139
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  • 64
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    Shock-tube thermochemistry tables for high-temperature gases. Volume 5: Carbon dioxide (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equilibrium thermodynamic properties and species concentrations for carbon dioxide are tabulated for moving, standing, and reflected shock waves. Initial pressures range from 6.665 to 6665 N/sq m (0.05 to 50.0 torr), and temperatures from 2,000 to over 80,000K. In this study, 20 molecular and atomic species were considered.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-135944 , JPL-TR-32-1408-VOL-5
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    A study of an advanced confined linear energy source (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A literature survey and a test program to develop and evaluate an advanced confined linear energy source were conducted. The advanced confined linear energy source is an explosive or pyrotechnic X-Cord (mild detonating fuse) supported inside a confining tube capable of being hermetically sealed and retaining all products of combustion. The energy released by initiation of the X-Cord is transmitted through the support material to the walls of the confining tube causing an appreciable change in cross sectional configuration and expansion of the tube. When located in an assembly that can accept and use the energy of the tube expansion, useful work is accomplished through fracture of a structure, movement of a load, reposition of a pin, release of a restraint, or similar action. The tube assembly imparts that energy without release of debris or gases from the device itself. This facet of the function is important to the protection of men or equipment located in close proximity to the system during the time of function.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-112096
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  • 66
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    Long life high reliability thermal control systems study data handbook (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of thermal control systems with high reliability and long service life is discussed. Various passive and semi-active thermal control systems which have been installed on space vehicles are described. The properties of the various coatings are presented in tabular form.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-123734
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  • 67
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    Mathematical modeling of high and low temperature heat pipes (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Following a review of heat and mass transfer theory relevant to heat pipe performance, math models are developed for calculating heat-transfer limitations of high-temperature heat pipes and heat-transfer limitations and temperature gradient of low temperature heat pipes. Calculated results are compared with the available experimental data from various sources to increase confidence in the present math models. Complete listings of two computer programs for high- and low-temperature heat pipes respectively are included. These programs enable the performance to be predicted of heat pipes with wrapped-screen, rectangular-groove, or screen-covered rectangular-groove wick.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-122419
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  • 68
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    The kinetics of reaction of the by-products of ablative materials at high temperatures and the rate of heat transfer between hot surfaces and reactive gases (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Research has been conducted by means of laboratory experiments to enhance understanding of the fundamental mechanisms of heterogeneous and homogeneous chemical reactions taking place during ablative processes that accompany the reentry or manned space vehicles into planetary atmospheres. Fundamental mechanisms of those chemical reactions believed to be important in the thermal degradation of ablative plastic heat shield materials, and the gases evolved, are described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-114453
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    Noise analysis of nucleate boiling (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The techniques of noise analysis have been utilized to investigate nucleate pool boiling. A simple experimental setup has been developed for obtaining the power spectrum of a nucleate boiling system. These techniques were first used to study single bubbles, and a method of relating the two-dimensional projected size and the local velocity of the bubbles to the auto-correlation functions is presented. This method is much less time consuming than conventional methods of measurement and has no probes to disturb the system. These techniques can be used to determine the contribution of evaporation to total heat flux in nucleate boiling. Also, these techniques can be used to investigate the effect of various parameters upon the frequency response of nucleate boiling. The predominant frequencies of the power spectrum correspond to the frequencies of bubble generation. The effects of heat input, degree of subcooling, and liquid surface tension upon the power spectra of a boiling system are presented. It was found that the degree of subcooling has a more pronounced effect upon bubble size than does heat flux. Also the effect of lowering surface tension can be sufficient to reduce the effect of the degree of subcooling upon the size of the bubbles.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-126382
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    Phase change materials handbook (1971)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: This handbook is intended to provide theory and data needed by the thermal design engineer to bridge the gap between research achievements and actual flight systems, within the limits of the current state of the art of phase change materials (PCM) technology. The relationship between PCM and more conventional thermal control techniques is described and numerous space and terrestrial applications of PCM are discussed. Material properties of the most promising PCMs are provided; the purposes and use of metallic filler materials in PCM composites are presented; and material compatibility considerations relevant to PCM design are included. The engineering considerations of PCM design are described, especially those pertaining to the thermodynamic and heat transfer phenomena peculiar to PCM design. Methods of obtaining data not currently available are presented. The special problems encountered in the space environment are described. Computational tools useful to the designer are discussed. In summary, each aspect of the PCM problem important to the design engineer is covered to the extent allowed by the scope of this effort and the state of the art.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-61363 , LMSC/HREC-D225138
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  • 71
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    Levitation calorimetry. IV - The thermodynamic properties of liquid cobalt and palladium. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Some of the thermodynamic properties of liquid cobalt and palladium investigated by means of levitation calorimetry are reported and discussed. The presented data include the specific heats and heats of fusion of the liquid metals, and the emissivities of the liquid metal surfaces.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Physical Chemistry; 75; Nov. 25
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  • 72
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    Transport properties of atomic hydrogen. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Determination of a new set of values for the coefficients of viscosity and thermal conductivity of atomic hydrogen in the range from 1 to 100,000 K. The estimated error is about 5%. Quantal theory was used for low temperatures and classical theory for high temperatures. There is excellent agreement between the two theories as low as 20 K.-
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Atomic Data; 3; Dec. 197
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    Compressibility measurements of gases using externally heated pressure vessels. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Most of the data collected under conditions of high temperature and pressure have been determined using a thick-walled bomb of carefully measured and fixed volume which is externally heated by an electric furnace or a thermostatically controlled bath. There are numerous variations on the basic method depending on the pressure-temperature range of interest, and the particular gas or gas mixture being studied. The construction and calibration of the apparatus is discussed, giving attention to the pressure vessel, the volume of the bomb, the measurement of pressure, the control and measurement of temperature, and the measurement of the amount and composition of gas in the bomb.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 74
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    An investigation of the solidification of a metal and two n-paraffins using an acoustic technique. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A novel acoustic technique is described for following the motion of the solid-liquid interface during the freezing of mercury, n-hexadecane and n-octadecane where heat transfer is unidirectional. It is shown that the actual amount of solidification occurring in a given time differs from that predicted using a numerical solution to the transient heat conduction problem. The differences are small for mercury but large for the paraffins. They are interpreted in terms of the nature of the solid-liquid interface. Furthermore the experimental and predicted temperature distributions in the liquid and solid phases differ. These differences are extremely small for mercury. The data for the three materials conform to a relationship observed previously according to which the thickness of the solidified layer is a linear function of the square root of time.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Applied Scientific Research; 25; Dec. 197
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  • 75
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    Thermal control and heat storage by melting and freezing. Space thermal control development (1971)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Current results of an experimental study of increasing phase change material thermal diffusivity by means of solid fillers are reported. Aluminum honeycomb appears to offer the best improvement of any of the fillers investigated to date. Details of the experimental method developed in the present study for rapidly determining thermal diffusivities with a precision of about 10 percent are also reported. Further concepts regarding phase change material thermal diffusivity enhancement and of phase change material operation are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-124214 , HREC-5183-1 , LMSC/HREC-D162884
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    Combustion dynamics in liquid rocket engines (1971)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A chemical analysis of the emission and absorption spectra in the combustion chamber of a nitrogen tetroxide/aerozine-50 rocket engine was conducted. Measurements were made under conditions of preignition, ignition, and post combustion operating periods. The cause of severe ignition overpressures sporadically observed during the vacuum startup of the Apollo reaction control system engine was investigated. The extent to which residual propellants or condensed intermediate reaction products remain after the engine has been operated in a pulse mode duty cycle was determined.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-128898 , DRI-2577
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  • 77
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    Radiative transfer effects on reflected shock waves. I - Transparent gas. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Analytical and numerical calculation of the effects of radiative cooling on the flow field and heat transfer behind a reflected shock wave. The analytical solutions are developed by an expansion procedure about the Newtonian limit - i.e., the flow variables are expanded in the small parameter epsilon representing the initial density ratio across the shock front. Solutions carried out through the zeroth- and first-orders in epsilon show an accuracy to the order of epsilon squared - namely, for the specific conditions considered the analytically calculated enthalpy changes agree to within 2% with the numerically computed changes. The numerical procedure consists of a finite-difference calculation with pressure gradients neglected. The analytical calculations show that pressure-gradient effects may be neglected, except at very long times when the shocked gas has cooled by a large amount. The present calculations show much greater shock-wave attenuation than does a previous numerical computation. This difference is attributed to a better representation of the thermodynamic properties in the present calculations.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-737423 , Physics of Fluids; 14; Dec. 197
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  • 78
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    A statistical mechanical calculation of the thermodynamic properties of interstitial solid solutions involving second nearest neighbor interactions. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A previous calculation of the thermodynamic properties of interstitial solid solutions based on the technique of Kirkwood expansions has been extended to include the effects of second nearest neighbor solute atom mutual interactions. The error inherent in the first order (or quasi-chemical) counting of the degeneracy of the solution crystal is avoided. It is shown that, at high temperatures, even strong second nearest neighbor solute mutual interactions have a negligible effect on the entropy of the solution and a small, temperature-dependent effect on the solute partial enthalpy.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Acta Metallurgica; 20; Jan. 197
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    Combustion of a premixed system in stagnation flow. I - Theoretical. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The theoretical steady-state and transient characteristics of a premixed combustible system in laminar axisymmetric stagnation flow are studied by way of numerical solution of the governing boundary-layer equations. Computations, which are based on the oxidation reaction of carbon monoxide in humid air, invoke a minimum of simplifying assumptions. Steady-state results include prediction of (1) profiles of the state variables, (2) extinction of blow-off conditions, (3) ignition conditions, and (4) the heat flux to the stagnation point. Computer simulations of the unsteady state provide an indication of the stability of a given steady state to perturbations. Comparisons between some of the predictions of the mathematical model and the results of laboratory experiments will be reported in Part II.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-743387 , AROD-5648-8-E , Combustion Science and Technology; 4; Nov. 197
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    Combustion stabilization with acoustic cavities. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An experimental and analytical study has been performed to develop the technology necessary for effective use of acoustic cavities to suppress acoustic modes of combustion instability. An unbaffled variation of the LM ascent engine has been made dynamically stable with acoustic cavities only; five different cavity configurations were found sufficient to produce dynamic stability. An analytical model was developed to calculate the damping contributed by the cavity. Further, subscale tests were made to determine the nonlinear acoustic impedance of these cavities.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 8; Dec. 197
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  • 81
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    Anode heat transfer in a constricted tube arc. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The complex energy exchange mechanisms occurring on the most severely heated component of an arc constrictor, the anode, have been investigated. Measurements performed to determine the anode heat flux for a cascade, atmospheric argon arc of the Maecker type are described. The results are used to check the validity of an existing anode heat transfer model.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 9; Dec. 197
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  • 82
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    Optimal startup control of a jacketed tubular reactor. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The optimal startup policy of a jacketed tubular reactor, in which a first-order, reversible, exothermic reaction takes place, is presented. A distributed maximum principle is presented for determining weak necessary conditions for optimality of a diffusional distributed parameter system. A numerical technique is developed for practical implementation of the distributed maximum principle. This involves the sequential solution of the state and adjoint equations, in conjunction with a functional gradient technique for iteratively improving the control function.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIChE Journal; 17; Nov. 197
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  • 83
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    Convective stability in the presence of a catalytic chemical reaction. I. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A linear analysis of hydrodynamic stability has been applied to a problem in which a fluid mixture is contained between two horizontal planes. One species diffuses to the lower plane where it is destroyed by a rapid exothermic or endothermic catalytic reaction. Results show that important coupling takes place between thermal and concentration fields. This coupling gives rise to unusual stabilizing or destabilizing effects, depending upon the value of Lewis number. Several examples are discussed. It is also shown how the results can be applied to other problems involving heat and mass transfer.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIChE Journal; 17; Nov. 197
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  • 84
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    The spectrum of steady state turbulent convection. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Based on Heisenberg's statistical theory of turbulence, a model for steady state turbulent convection is herein proposed, and on the basis of this model, equations for the energy spectrum for steady state turbulent convection are derived. The spectrum is obtained from the solution of a nonlinear integral equation. After the integral equation is brought into a universally valid nondimensional form, it is transformed into a nonlinear first order differential equation to be solved numerically, with the Rayleigh number appearing as the only parameter. The energy spectrum has a substantial deviation from the Kolmogoroff law, as a result of the buoyancy force acting on the rising and falling eddies. The presented theory may be applicable to convection in planetary and stellar atmospheres wherein the radiative heat transport is small.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Zeitschrift fuer Naturforschung; vol. 26a
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  • 85
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    Mathematical modeling of high and low temperature heat pipes (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mathematical models are developed for calculating heat-transfer limitations of high-temperature heat pipes and heat-transfer limitations and temperature gradient of low temperature heat pipes. Calculated results are compared with the available experimental data from various sources to increase confidence in the present math models. Complete listings of two computer programs for high- and low-temperature heat pipes respectively are appended. These programs enable the performance of heat pipes with wrapped-screen, rectangular-groove or screen-covered rectangular-groove wick to be predicted.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-126739
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  • 86
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    Cryogenic research at MSFC: Research achievements review, Volume 4 no. 2 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Cryogenic research applicable to Skylab, space station, and space shuttle programs
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-64561
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  • 87
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    Pyrotechnic hazards classification and evaluation program. Electrostatic vulnerability of the E8 and XM15/XM165 clusters, phase 2 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation into the electrostatic phenomena associated with the manufacturing and handling of explosives is discussed. The testing includes measurement of the severity of the primary charge generation mechanism, triboelectric effects between dissimilar surfaces; refinement of equivalent circuits of the XM15/XM165 and E8 fuse trains; evaluation of the electrostatic spark discharge characteristics predicted by an equivalent circuit analysis; and determination of the spark ignition sensitivity of materials, components, junctions, and subassemblies which compose the XM15/XM165 and E8 units. Special studies were also performed. These special tests included ignition sensitivity of the complete XM15 fuse train when subjected to discharges through its entire length, measurement of electrostatic potentials which occur during the E8 foaming operation during fabrication, and investigation of the inadvertent functioning of an XM15 cluster during manufacturing. The test results are discussed and related to the effectiveness of suggested modification to reduce the electrostatic ignition sensitivity.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-123040 , GE-MTSD-R-057
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  • 88
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    Pyrotechnic hazards classification and evaluation program. Phase 2, segment 3: Test plan for determining hazards associated with pyrotechnic manufacturing processes (1971)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A comprehensive test plan for determining the hazards associated with pyrotechnic manufacturing processes is presented. The rationale for each test is based on a systematic analysis of historical accounts of accidents and a detailed study of the characteristics of each manufacturing process. The most hazardous manufacturing operations have been determined to be pressing, mixing, reaming, and filling. The hazard potential of a given situation is evaluated in terms of the probabilities of initiation, communication, and transition to detonation (ICT). The characteristics which affect the ICT probabilities include the ignition mechanisms which are present either in normal or abnormal operation, the condition and properties of the pyrotechnic material, and the configuration of the processing equipment. Analytic expressions are derived which describe the physical conditions of the system, thus permitting a variety of processes to be evaluated in terms of a small number of experiments.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-122978 , GE-MTSD-R-054
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  • 89
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    Pyrotechnic hazards classification and evaluation program test report. Heat flux study of deflagrating pyrotechnic munitions (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat flux study of deflagrating pyrotechnic munitions is presented. Three tests were authorized to investigate whether heat flux measurements may be used as effective hazards evaluation criteria to determine safe quantity distances for pyrotechnics. A passive sensor study was conducted simultaneously to investigate their usefulness in recording events and conditions. It was concluded that heat flux measurements can effectively be used to evaluate hazards criteria and that passive sensors are an inexpensive tool to record certain events in the vicinity of deflagrating pyrotechnic stacks.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-122980 , GE-MTSD-R-061
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  • 90
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    Investigation of hazards associated with plastic bonded starter mix manufacturing processes (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation to determine the hazards potential evaluation of plastic bonded starter mix (PBSM) production processes and the application to the M18 and M7A3 grenades is reported. The investigation indicated: (1) the materials with the greatest hazards characteristics, (2) process operating stations most likely to initiate hazardous conditions, (3) the test program required to examine ignition characteristics and process hazards, and (4) the method of handling the accumulated information from testing and safety analyses.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-122977 , GE-MTSD-R-064
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  • 91
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    Pyrotechnic hazards classification and evaluation program. Phase 3, segments 1-4: Investigation of sensitivity test methods and procedures for pyrotechnic hazards evaluation and classification, part A (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The findings, conclusions, and recommendations relative to the investigations conducted to evaluate tests for classifying pyrotechnic materials and end items as to their hazard potential are presented. Information required to establish an applicable means of determining the potential hazards of pyrotechnics is described. Hazard evaluations are based on the peak overpressure or impulse resulting from the explosion as a function of distance from the source. Other hazard classification tests include dust ignition sensitivity, impact ignition sensitivity, spark ignition sensitivity, and differential thermal analysis.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-122979 , GE-MTSD-R-059-PT-A
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  • 92
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    Pyrotechnic hazards classification and evaluation program. Run-up reaction testing in pyrotechnic dust suspensions (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary investigation of the parameters included in run-up dust reactions is presented. Two types of tests were conducted: (1) ignition criteria of large bulk pyrotechnic dusts, and (2) optimal run-up conditions of large bulk pyrotechnic dusts. These tests were used to evaluate the order of magnitude and gross scale requirements needed to induce run-up reactions in pyrotechnic dusts and to simulate at reduced scale an accident that occurred in a manufacturing installation. Test results showed that propagation of pyrotechnic dust clouds resulted in a fireball of relatively long duration and large size. In addition, a plane wave front was observed to travel down the length of the gallery.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-123039 , GE-MTSD-R-062
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  • 93
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    Stagnation region heating of a phenolic-nylon ablator during return from planetary missions (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a stagnation-line analysis of the radiative heating of a phenolic-nylon ablator are reported. The analysis includes flowfield coupling with the ablator surface, equilibrium chemistry, multicomponent or binary diffusion and a coupled line and continuum radiation calculations. Users manual and operating instructions for the computer programs listed in the report are included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-112026
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  • 94
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    Arterial and grooved cryogenic heat pipes. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Tests were conducted on two cryogenic heat pipes using nitrogen as the working fluid. Both pipes are 1.27 cm in diameter. The first pipe is 141 cm long and uses longitudinal grooves in the aluminum wall as the wick structure. The second pipe is 91 cm long and has an arterial wick adjacent to the wall. In addition, circumferential screw threads are machined along the entire length of the inside pipe wall. Both heat pipes primed with no difficulty in the horizontal position. Start-up after burn-out was obtained repeatedly. However, more testing is required to determine whether the artery pipe is as reliable as the grooved pipe with respect to priming. Once primed, the artery heat pipe is much less sensitive to elevation than the grooved design and, consequently, offers a significant advantage with respect to ground testing. Heat-transfer characteristics of the two pipes were comparable, with both pipes achieving the initial goal of 1000 watt-cm of heat-transport capability.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-WA/HT-42
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  • 95
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    Heat transfer and forces on concave surfaces in free molecule flow. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A Monte Carlo modeling technique is described for mathematically simulating free molecular flows over a concave spherical surface and a concave cylindrical surface of finite length. The half-angle of the surfaces may vary from 0 to 90 degrees, and the incident flow may have an arbitrary speed ratio and an arbitrary angle of attack. Partial diffuse reflection and imperfect energy accommodation for molecules colliding with the surfaces are also considered. Results of heat transfer, drag and lift coefficients are presented for a variety of flow conditions. The present Monte Carlo results are shown to be in very good agreement with certain available theoretical solutions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-WA/HT-17
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  • 96
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    Steady-state temperature distribution in living tissue modeled as cylindrical shells. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Closed form, analytical solutions to the problem of steady-state heat transfer in living tissue modeled as cylindrical shells are presented and discussed. These solutions are particularly useful for the study of temperature distributions in the extremities. Metabolic heat generation, conduction, and heat transported by the blood perfusing the tissue are considered in the model. The results demonstrate the important role that the blood stream plays in the transfer of heat inside living tissue. Solutions are also presented for the limiting cases of diminishing blood flow that would occur during vasoconstriction or occlusion of blood by external means.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-WA/HT-34
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  • 97
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    Test of 50-kw heat-pipe radiator. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A heat pipe radiator consisting of 100 sodium-filled, 1.91-cm OD, stainless steel heat pipes has been tested at temperatures up to 760 C. This radiator was initially designed to have a heat pipe temperature of 740 C with a central coolant channel temperature of 771 C. The as-fabricated radiator heat pipe temperatures varied from 605 C to 700 C when the central coolant channel average temperature was 740 C. The heat pipes operated at 25 C to 110 C lower-than-expected temperatures, resulting in a 43 kW heat rejection capability vs the 50 kW design goal and the 65 kW ultimate capability of the radiator. The 43 kW heat rejection yields a mass/heat rejection ratio of 0.182 kg/kWt which is good for this early state-of-the-art heat pipe radiator. An end-of-mission life specific weight of 0.154 kg/kW is apparently achievable with improvements in radiator fabrication and brazing techniques.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-WA/HT-16
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    A systematic exposition of the conservation equations for blast waves. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: In order to provide a rational background for the analysis of experimental observations of blast wave phenomena, the conservation equations governing their nonsteady flow field are formulated in a general manner, without the usual restrictions imposed by an equation of state, and with proper account taken, by means of source terms, of other effects which, besides the inertial terms that conventionally dominate these equations, can affect the flow. Taking advantage of the fact that a blast wave can be generally considered as a spatially one-dimensional flow field whose nonsteady behavior can be regarded, consequently, as a function of just two independent variables, two generalized blast wave coordinates are introduced, one associated with the front of the blast wave and the other with its flow field. The conservation equations are accordingly transformed into this coordinate system, acquiring thereby a comprehensive character, in that they refer then to any frame of reference, being applicable, in particular, to problems involving either space or time profiles of the gas-dynamic parameters in the Eulerian system, or time profiles in the Lagrangian system.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-WA/APM-1 , AD-739119 , AFOSR-72-0673TR
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  • 99
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    Mathematical analysis of a Vuilleumier refrigerator. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A comprehensive analysis of the Vuilleumier refrigerator was conducted. This analysis includes the effects of nonisothermal gas heat addition and rejection, hot and cold regenerator inefficiencies, conduction losses, and gas leakage losses. A computer program was written which solves the equations resulting from the analysis. The program calculates internal pressures, temperatures, and gas flow rates as functions of refrigerator crank angle, as well as overall refrigerator cooling load and power input. Comparisons between the program results and available data show good agreement, with a marked improvement over the predictions of the ideal model.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-WA/HT-33
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    Calculation of inviscid surface streamlines and heat transfer on shuttle type configurations. Part 2: Description of computer program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of the computer program used for heating rate calculation for blunt bodies in hypersonic flow is given. The main program and each subprogram are described by defining the pertinent symbols involved and presenting a detailed flow diagram and complete computer program listing. Input and output parameters are discussed in detail. Listings are given for the computation of heating rates on (1) a blunted 15 deg half-angle cone at 20 deg incidence and Mach 10.6, (2) a blunted 70 deg slab delta wing at 10 deg incidence and Mach 8, and (3) the HL-10 lifting body at 20 deg incidence and Mach 10. In addition, the computer program output for two streamlines on the blunted 15 deg half-angle cone is listed. For Part 1, see N71-36186.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-111922
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