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  • Other Sources  (2,819)
  • PROPULSION SYSTEMS  (1,456)
  • THERMODYNAMICS AND COMBUSTION  (1,363)
  • General Chemistry
  • 1970-1974  (2,819)
Collection
Source
Keywords
Years
Year
  • 101
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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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    NASA TECHNICAL REPORTS
  • 102
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    Nonisotropic exchange coefficients in turbulent swirling flames from mean value distributions (1971)
    In:  Other Sources
    Details
    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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  • 103
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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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  • 104
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    The effect of high-frequency periodic disturbances on axisymmetric wake diffusion flames (1971)
    In:  Other Sources
    Details
    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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  • 105
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    The radiation of sound from an engine exhaust (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Internal combustion engine exhaust system sound radiation, discussing pressure wave effects, energy flux and boundary conditions
    Keywords: PROPULSION SYSTEMS
    Type: ; BROTECHNIKA, NO. 2(
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  • 106
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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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  • 107
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    A comparison of boundary-layer transition data from temperature-sensitive paint and thermocouple techniques (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Temperature sensitive paint and thermocouple techniques comparison for boundary layer transition data, considering aerodynamic heating and transition Reynolds numbers
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
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  • 108
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    Film cooling effectiveness in hypersonic turbulent flow (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Film cooling effectiveness in hypersonic turbulent flow from downstream surface equilibrium temperature measurement
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; UGREVUE(
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  • 109
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    Auxiliary power unit - Introduction (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Program for developing hydrogen-oxygen fueled auxiliary power unit for space shuttle vehicle
    Keywords: PROPULSION SYSTEMS
    Type: PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 3 28 APR. 1971; P 1097-1098
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  • 110
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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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  • 111
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    Thermal constriction resistance due to non- uniform surface conditions - Contact resistance at non-uniform interface pressure (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Thermal constriction resistance due to nonuniform metal surface conditions, considering macroscopic contact resistance for nonuniform interface pressure distribution
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; VIGATION (
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  • 112
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    Radiative cooling of shock-heated air in cylindrical shock tubes (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Radiative cooling of shock heated air in cylindrical shock tubes, calculating enthalpy profiles for nonadiabatic air flow
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; UGREVUE(
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  • 113
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    TOPS spacecraft propulsion subsystem (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Trajectory correction propulsion subsystem /TCPS/, attitude propulsion subsystem /APS/ and pyrotechnic subsystem of thermoelectric outer planet spacecraft /TOPS/
    Keywords: PROPULSION SYSTEMS
    Type: ; ADEMIE DES SCIENCES
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  • 114
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    Laminar heating in interior corners at Mach 19 (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Laminar heating in hypersonic vehicles interior corners, analyzing helium tunnel heat transfer data for various intersecting wedge corners
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; ACE(
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  • 115
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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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  • 116
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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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  • 117
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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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  • 118
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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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  • 119
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    Thermal emissivity and solar absorptivity of aluminum coated with double layers of aluminum oxide and silicon oxide (1971)
    In:  Other Sources
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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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  • 120
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    A method of treating the nongray error in total emittance measurements (1971)
    In:  Other Sources
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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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  • 121
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    Review of SERT II power conditioning (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: SERT 2 power conditioning, describing operating requirements, components construction, overload protection, system performance, etc
    Keywords: PROPULSION SYSTEMS
    Type: ; 6-8, 10-16 (
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  • 122
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    Ablation and luminosity of artificial meteors (1971)
    In:  Other Sources
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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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  • 123
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    Relationship between temperature and velocity profiles in a turbulent boundary layer along a supersonic nozzle with heat transfer (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Turbulent boundary layer air flow through supersonic convergent-divergent nozzle with heat transfer, considering relationship between temperature and velocity profiles
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; UGREVUE(
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  • 124
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    Development status of reusable nonmetallic thermal protection (1971)
    In:  Other Sources
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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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  • 125
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    Plume impingement during separation of a two stage space shuttle vehicle (1971)
    In:  Other Sources
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    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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  • 126
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    Shock interference heating on the space shuttle booster during ascent (1971)
    In:  Other Sources
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    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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  • 127
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    Shock interference heating and density-ratio effects. Part 1 - Flow field visualization, thermocouple measurements, and analysis (1971)
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    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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  • 128
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    An analysis of predicted space shuttle temperatures and their impact on thermal protection systems (1971)
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    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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  • 129
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    Shock interference heating and density ratio effects. Part 2 - Hypersonic density ratio effects (1971)
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    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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  • 130
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    Analysis of the longitudinal high frequency stability of a staged combustion cycle, Appendix B (1971)
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    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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  • 131
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    Nonequilibrium boundary layer at a stagnation point for a hydrogen-helium stream over ablating graphite (1974)
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    Publication Date: 2011-08-16
    Description: The nonequilibrium axisymmetric stagnation point boundary layer over an ablating graphite surface is considered. The external stream is a high temperature mixture of hydrogen and helium. Variable thermodynamic and transport properties are assumed. Lennard-Jones potential model is used to calculate the transport coefficients of each species. Although the mixture rules for viscosity of the gas mixture are used, the weighting functions are more sophisticated than those commonly employed. For the conductivity of the mixture, generalized Wassiljewa coefficients are used. Seven species with 28 dissociation/recombination reactions are considered. Hansen's model for the dissociation rate constants is employed. The recombination rate constants are obtained by invoking detailed balance principles assisted by the JANAF thermodynamic data and the Hansen-Pearson thermodynamic data for C3.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Acta Astronautica; 1; Mar
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  • 132
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    Effect of wall temperature spatial variations on aerodynamic heating to an actively cooled aircraft (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The design of cooled skin panels, which requires consideration of many parameters such as heat load, skin thickness, panel size, tube spacing, tube size, temperature limits, coolant flow, etc., must minimize weight and thermal stresses. A design procedure for such panels has been developed by Bell Aerospace Company (Helenbrook and Anthony, 1971). This design procedure assumes a uniform heating rate to the panel, i.e., the variation of aerodynamic heating rate due to the cyclic wall temperature distribution, which results from the discrete coolant tube locations in such a panel, has been neglected. This study was made to determine if these variations were sufficiently large to cause variations in aerodynamic heating rate which would require coupling of boundary layer and conductive thermal analysis solutions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Aircraft; 11; Aug. 197
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  • 133
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    Chemical propulsion - The old and the new challenges (1973)
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    Publication Date: 2011-08-16
    Description: The historical background concerning the application of liquid propellant rockets is considered. Progress to date in chemical liquid propellant rocket engines can be summarized as an increase in performance through the use of more energetic propellant combinations and increased combustion pressure. New advances regarding liquid propellant rocket engines are related to the requirement for reusability in connection with the development of the Space Shuttle.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Student Journal; 11; Dec. 197
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  • 134
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    Electric propulsion - Now (1974)
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    Publication Date: 2011-08-16
    Description: The state of the art of electric propulsion technology is discussed with a review of the many difficult engineering problems which must be resolved before the incorporation of electric propulsion in space missions. Interferences with the spacecraft and its scientific instrumentation, conducted and radiated electromagnetic interferences during the switching and processing of large electrical loads, and mercury and other eroded materials deposition on the spacecraft are indicated among the engineering and design challenges to be overcome and resolved.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Student Journal; 12; Apr. 197
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  • 135
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    Quiet engine from NASA (1974)
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    Publication Date: 2011-08-16
    Description: Engine designs resulting from the NASA sponsored quiet engine program are described in terms of their possible use on the DC-8. These engines have high bypass ratios for low jet noise and low-speed, low-noise fans. Experiments were carried out on various fan designs with different tip speeds. The advantage of low tip speeds and high lift coefficients has been demonstrated. The engines are equipped with flight-standard nacelles with acoustic suppression. It is estimated that these improvements will reduce DC-8 noise by about 26EPNdB-29EPNdB.
    Keywords: PROPULSION SYSTEMS
    Type: Flight International; 106; July 25
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  • 136
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    Finite-amplitude thermal convection in a spherical shell (1974)
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    Publication Date: 2011-08-16
    Description: The properties of finite-amplitude thermal convection for a Boussinesq fluid contained in a spherical shell are investigated. All nonlinear terms are retained in the equations, and both axisymmetric and nonaxisymmetric solutions are studied. The velocity is expanded in terms of poloidal and toroidal vectors. Spherical surface harmonics resolve the horizontal structure of the flow, but finite differences are used in the vertical. With a few modifications, the transform method developed by Orszag (1970) is used to calculate the nonlinear terms, while Green's function techniques are applied to the poloidal equation and diffusion terms.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Fluid Mechanics; 63; May 15
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  • 137
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    On the propagation velocity of a detonation-shock combined wave (1974)
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    Publication Date: 2011-08-16
    Description: A quasi-one-dimensional analysis and a generalized Chapman-Jouguet condition are developed for a gaseous free detonation in an inert environment. Two characteristic features derived from the results are that there exists a lower limit on the heat of combustion, the charge diameter, and the molecular weight of the ambient gas and that there are two propagation velocities for a parameter combination above a certain critical value. Therefore the detonation failure of a free gas column is a hydrodynamic rather than a chemical phenomenon.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Zeitschrift fuer angewandte Mathematik und Mechanik; 54; Mar. 197
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  • 138
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    Swept-slot film-cooling effectiveness in hypersonic turbulent flow (1974)
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    Publication Date: 2011-08-16
    Description: Measurement results are presented for the surface equilibrium temperature downstream of swept slots, with sonic tangential air injection into a thick hypersonic turbulent boundary layer. These results are compared with unswept slot results for cooling effectiveness.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
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  • 139
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    Mean flow development and surface heating for an attaching compressible free shear layer (1974)
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
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  • 140
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    Putting all our noise technology to work (1974)
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    Publication Date: 2011-08-16
    Description: An assessment of the present state of the art in noise reduction technology indicates that this technology has the potential for effectively attaining this goal - a conclusion that is in apparent conflict with the frequently voiced complaints on intolerable noise levels near airports. Measures are suggested for a more vigorous implementation of available technology in practice to combat the aircraft noise problem.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 12; Jan. 197
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  • 141
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    Lambda-point measurements of eta rho sub n for pure He 4 and for three He 3-He 4 mixtures. (1972)
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    Publication Date: 2011-08-16
    Description: Results of torsional crystal measurements of eta rho sub n for pure He 4 and for three He 3-He 4 mixtures over temperature intervals which included their respective lambda points. The precision of the measurements for the mixtures was greater than that of any previous lambda-point eta rho sub n measurements. Doubly reduced plots of eta rho sub n versus T showed a slight but definite tendency for such curves to rotate clockwise about the (1,1) point with increasing x sub 3 up to about 0.05. Values of eta were derived from the measurements by computing rho sub n as a function of T*. For each mixture, both eta and d eta/dT were continuous across T sub lambda (x sub 3). No tendency was manifest for such curves to develop discontinuities as x sub 3 decreased. It was therefore inferred that both eta and d eta/dT of pure He 4 are continuous across T sub lambda (0).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physical Review A - General Physics; vol. 5
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  • 142
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    Thermodynamic properties and nozzle flow of hydrogen to 1000 atm and 100,000 K (1971)
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    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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  • 143
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    Radiative cooling of shock-heated air in an explosively driven shock tube. (1972)
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    Publication Date: 2011-08-16
    Description: Results are presented of an experimental program to measure the effect of radiative cooling on the enthalpy distribution behind incident shock waves traveling in air. The shock velocity was nominally 16 km/sec and the preshock ambient pressure was varied from 0.4 to 1.6 torr. Shock-tube diameters of 4.7 and 9.4 cm were used to investigate the effects of varying optical depths. Radiative cooling rates were determined from spatially resolved measurements of the profile of the H sub alpha line and from absolute measurements of the continuum radiation. The measured enthalpy profiles are in good agreement with the theoretical predictions of Chien and Compton which account for both nongrey and multidimensional aspects of the radiative transport in the shock tube.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 15; Jan. 197
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  • 144
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    Preliminary results of large supersonic burning combustor testing. (1972)
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    Publication Date: 2011-08-16
    Description: A hydrogen fueled supersonic-burning combustor 18 in. in diameter, which is equivalent to that of an engine about 6 ft in diameter, was tested as a direct-connected duct at inlet conditions which simulated Mach 8 flight at 115,000 ft alt. A synthetic air consisting of oxygen with 39% nitrogen and 38% water vapor at a total temperature of 4500 deg R and a total pressure of 300 psia was supplied to the combustor inlet by a hydrazine-nitrogen tetroxide hot gas generator which maintained a uniform inlet flow Mach number of 2.8. The large combustor size required a new approach to fuel injector design. Some hydrogen was injected through flush-wall injectors, but most was injected from two rows of swept and tapered struts immersed in the flow stream. Supersonic combustion was obtained at hydrogen equivalence ratios of 0.94 without encountering thermal cho king. Wall static pressures, and the radial distribution of hydrogen, Pitot pressure, and Mach number were determined at the combustor exit.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Aircraft; 9; Jan. 197
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  • 145
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    Kinetic limitations on the diffusional control theory of the ablation rate of carbon. (1971)
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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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  • 146
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    Thin wing corrections for phase-change heat-transfer data. (1971)
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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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  • 147
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    Criteria for electrically heated temperature probes in flames. (1971)
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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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  • 148
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    The NASA Quiet Engine Programme. (1971)
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    Publication Date: 2011-08-16
    Description: Discussion of the experimental Quiet Engine developed under the NASA program to reduce jet aircraft noise levels. The current status of the program is given as follows: Aerodynamic evaluation of the three fans is complete and their acoustic evaluation is partially complete. Tests of fan casing boundary-layer section and of serrated leading edges on the half-scale B fan are complete and are underway on the half-scale C fan. Tests of the first engine with the A fan began in August 1971.
    Keywords: PROPULSION SYSTEMS
    Type: Interavia; 26; Dec. 197
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  • 149
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    Airbreathing propulsion system trends. (1971)
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    Publication Date: 2011-08-16
    Description: Among trends in airbreathing propulsion, the priority is shown to belong to the goal of quieting engines to a level no greater than the natural background noise level of the environment in which they operate. For military engines, not so severely noise-constrained, the possibility of stoichiometric gas-turbine engines is shown to be within reach. Very high bypass ratio propfans are especially suitable for V/STOL aircraft. Evolution of reliable variable-geometry inlets and exhaust nozzles characterizes trends in the supersonic regime.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 9; Nov. 197
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  • 150
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    New half-range differential approximation for spherically-symmetric radiative transfer. (1971)
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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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  • 151
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    Stability of plane Poiseuille flow with heat transfer. (1972)
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    Publication Date: 2011-08-16
    Description: Investigation of the influence of heat transfer on the stability of a plane Poiseuille flow iahnnl. The liquid flow is affected by the heat transfer through the variation in viscosity with temperature. Additional viscosity gradient terms are included in a modified Orr-Sommerfeld equation, and it is the presence of these terms which leads to a prediction of more unstable flows, for without the inclusion of these extra terms, the flow is stabilized. The results show that a temperature difference between the walls is always destabilizing and, in particular, a temperature difference between the walls of 100 F leads to a reduction in the critical Reynolds number from 7800 to 4600.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 15; Mar. 197
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  • 152
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    Thermal radiation heat transfer. (1972)
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    Publication Date: 2011-08-16
    Description: A comprehensive discussion of heat transfer by thermal radiation is presented, including the radiative behavior of materials, radiation between surfaces, and gas radiation. Among the topics considered are property prediction by electromagnetic theory, the observed properties of solid materials, radiation in the presence of other modes of energy transfer, the equations of transfer for an absorbing-emitting gas, and radiative transfer in scattering and absorbing media. Also considered are radiation exchange between black isothermal surfaces, radiation exchange in enclosures composed of diffuse gray surfaces and in enclosures having some specularly reflecting surfaces, and radiation exchange between nondiffuse nongray surfaces. The use of the Monte Carlo technique in solving radiant-exchange problems and problems of radiative transfer through absorbing-emitting media is explained.
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  • 153
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    Technology for low noise aircraft - The NASA Quiet Engines (1973)
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    Publication Date: 2011-08-16
    Description: Review of the major goals, procedures, and results of the Quiet Engine Program that was initiated four years ago and is now nearing completion. This program has developed and demonstrated, in full-scale, experimental engine tests, technology advances which, if applied to the design of future aircraft, will help produce equipment with noise levels considerably lower than the older narrow-body aircraft and significantly lower than the new wide-body aircraft flying at present. However, the application of this noise reduction technology will result in increases in aircraft operating costs. Future aircraft noise reduction research should, therefore, consider improvements in the economics associated with noise reduction technology.
    Keywords: PROPULSION SYSTEMS
    Type: Noise Control Engineering; 1; Autumn 1
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  • 154
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    New horizons in chemical propulsion (1973)
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    Publication Date: 2011-08-16
    Description: After a review of the work of the late-Fifties on free radicals for propulsion, it is concluded that atomic hydrogen would provide a potentially large increase in specific impulse. Work conducted to find an approach for isolating atomic hydrogen is considered. Other possibilities for obtaining propellants of greatly increased capability might be connected with the technology for the generation of activated states of gases, metallic hydrogen, fuels obtained from other planets, and laser transfer of energy.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 11; Dec. 197
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  • 155
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    Transitional and turbulent heat transfer correlations for a lifting entry vehicle at Mach 10 (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Applicability of boundary layer transition and turbulent heat transfer data for lifting reentry vehicle at hypersonic speed to space shuttles
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA, WASHINGTON SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 1 JUL. 1970; P 418-443
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  • 156
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    Planetary exploration SRT - Advanced technical development (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Berylliumized propellant and hydrazine vernier engine for Jupiter Orbiter propulsion system
    Keywords: PROPULSION SYSTEMS
    Type: RES. AND ADVANCED DEVELOP. 31 AUG. 1970; P 43-209
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  • 157
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    Use of discrete sonic jets as boundary-layer trips in hypersonic flow (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Discrete sonic jets as boundary layer trips producing turbulent hypersonic flows with negligible intrinsic drag and downstream distortions
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; SEARCH(
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  • 158
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    Effect of water vapor on the combustion of flash-heated beryllium droplets (1970)
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    Publication Date: 2011-08-16
    Description: Oxide transport and water vapor effects on flash- heated beryllium droplet combustion
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; UGREVUE(
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  • 159
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    Thermal conductivity of gases - Organic compounds at atmospheric pressure (1970)
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    Publication Date: 2011-08-16
    Description: Thermal conductivity for organic compound gases at atmospheric pressure
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; VIGATION (
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  • 160
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    Radiant cooling (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Passive radiant cooler design involving patch cone radiative coupling calculation based on specular image technique
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; 459 (
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  • 161
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    Liquid rocket technology for the ch. e. (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Liquid rocket technology for chemical engineers, discussing propellant tanks, lines and valves, tank pressurization, turbopumps and combustion chamber problems
    Keywords: PROPULSION SYSTEMS
    Type: ; YAL SOCIETY (
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  • 162
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    Assessment of the explosive hazards of large solid rocket motors (1970)
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    Publication Date: 2011-08-16
    Description: Solid rocket motors potential hazards explosive reactions and temperature and blast effects
    Keywords: PROPULSION SYSTEMS
    Type: ; YSICA STATUS SOLIDI
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  • 163
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    Imperfect gas effect in real hydrogen drives (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Real hydrogen driver performance, analyzing intermolecular forces effects under high compression and heat
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; ADEMIE DES SCIENCES
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  • 164
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    Viscosity of binary polar-gas mixtures (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Approximate formula for viscosity of binary polar gas mixtures confirmed for unlike cross sections
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; SEARCH(
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  • 165
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    Effect of shear on duct wall impedance. (1973)
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    Publication Date: 2011-08-16
    Description: The solution to the equation governing the propagation of sound in a uniform shear layer is expressed in terms of parabolic cylinder functions. This result is used to develop a closed-form solution for acoustic wall impedance which accounts for both the duct liner and the presence of a boundary layer in the duct. The effective wall impedance can then be used as the boundary condition for the much simpler problem of sound propagation in uniform flow.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Sound and Vibration; 30; Sept. 8
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  • 166
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    Solar heating and cooling buildings (1973)
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    Publication Date: 2011-08-16
    Description: Sunshine is available in differing amounts everywhere in the world and the easiest method of capturing it is by absorption in the form of thermal energy (heat). Therefore, it is logical to utilize it directly in the heating and cooling of buildings and avoid losses that would occur by conversion to some other form. It may be emphasized that of the total energy consumed annually in the U.S., about 25% is used for heating and cooling in buildings. It is generally agreed that of all the possible widespread uses of solar energy, this application has the highest probability of success in the near term. Although there are significant uncertainties associated with some technological and economic aspects, they do not loom as large as those associated with other potentially significant applications, such as electrical power generation. It may, however, be noted that solar electrical power generation at the building site, or at a centralized station is an excellent long term prospect. Approximately 25 experimental solar heated structures have been built in various parts of the world.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: TERRASTAR: Terrest. Appl. of Solar Technol. and Res.; 28 p
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  • 167
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    Shape of porous cooled region for surface heat flux and temperature both specified. (1973)
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 16; Sept
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  • 168
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    Assessment of chemical nonequilibrium for massively ablating graphite. (1973)
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    Publication Date: 2011-08-16
    Description: Several types of artificial graphite have been irradiated by laser pulses in vacuum, and the composition of the resulting vapor cloud has been determined in situ by mass spectrometric techniques in order to gain information pertaining to nonequilibrium ablation of graphitic probes entering planetary atmospheres. Results are discussed in terms of variations in concentrations of carbon species from their equilibrium values, and plotted curves illustrate the effect of nonequilibrium ablation on radiative shielding for simulated Jupiter entry conditions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; Aug. 197
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  • 169
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    Transient forced convection heat transfer from an isothermal flat plate. (1973)
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    Publication Date: 2011-08-16
    Description: An analysis is presented for laminar transient forced-convection heat transfer from a horizontal flat plate. The presented analysis results include transient velocity and temperature profiles, boundary-layer growth rate, and heat-transfer rate with time.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; June 197
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  • 170
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    A review of film boiling at cryogenic temperatures. (1972)
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    Publication Date: 2011-08-16
    Description: Film boiling occurs in the quenching of metals, the chilling of biological species, the regenerative cooling of rockets, and the cooling down of a cryogenic fuel tank. Occasionally film boiling is also found in a nuclear reactor or in a cryomagnet. Aspects of film boiling involving an unconstrained liquid mass are considered, giving attention to the evaporation time, the Leidenfrost temperature, solid-liquid contacts, the thermal properties of the solid, effects of coating or scale, wettability, the metastable condition, and the velocity effect on drops. Developments discussed with regard to pool boiling are related to vertical surfaces, film boiling from horizontal surfaces, film boiling from a horizontal cylinder, film boiling from a sphere, and film boiling of helium. Processes of film boiling in a channel are also analyzed.
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  • 171
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    Effect on supersonic jet noise of nozzle plenum pressure fluctuations. (1972)
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    Publication Date: 2011-08-16
    Description: Demonstration that pressure fluctuations in the plenum chamber to a supersonic nozzle can strongly increase the noise radiated from the jet plume. The correlation shows that jet noise acoustic efficiency increases from 0.3% to 0.8% (or 4 dB) when the chamber roughness intensity increases from essentially no plenum chamber roughness to 2%. A roughness level of 2% has been observed in some turbojet engines. It is concluded that the reduction or elimination of plenum chamber pressure fluctuations may be an important method of reducing the total noise from jet engines.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 10; July 197
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  • 172
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    Minimum weight passive insulation requirements for hypersonic cruise vehicles. (1972)
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    Publication Date: 2011-08-16
    Description: Analytical solutions are derived for two representative cases of the transient heat conduction equation to determine the minimum weight requirements for passive insulation systems of hypersonic cruise vehicles. The cases discussed are the wet wall case with the interior wall temperature held to that of the boiling point of the fuel throughout the flight, and the dry wall case where the heat transferred through the insulation is absorbed by the interior structure whose temperature is allowed to rise.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 10; July 197
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  • 173
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    Evolution of the heat transfer and flow in moderately short turbulent boundary layers in severe pressure gradients (1974)
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 17; Sept
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  • 174
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    Aerodynamic heat transfer to RSI tile surfaces and gap intersections (1974)
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    Publication Date: 2011-08-16
    Description: Review of the results of aerothermal heating tests of a simulated reusable surface insulation (RSI) tile array, performed on the sidewall of a Mach-10 hypersonic tunnel. In particular, the heating characteristics of the tile array, such as they result from heating inside the tile-expansion-space providing gaps between individual tiles, are investigated. The results include the finding that heating on the upstream face of a tile is strongly affected by the interacting longitudinal gap flow.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; June 197
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  • 175
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    Nonlinear unsteady contact heat conduction of two-layer shells in the presence of thermal radiation (1974)
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    Publication Date: 2011-08-16
    Description: A technique is proposed for calculating the complex heat transfer of mated shells with the surrounding medium which also takes into account the temperature dependence of the contact thermal resistance between the shells. This technique can be used for thermal calculations and for calculations of the temperature stresses in two-layer space structure shells.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 169-177
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  • 176
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    Radiative cooling of bodies of arbitrary shape and variable volume in vacuum (1974)
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    Publication Date: 2011-08-16
    Description: On the basis of joint application of the Tolubinskii integral method and the perturbation method, the asymptotic unsteady temperature distribution is constructed for a region of arbitrary shape on the moving boundary of which there are located nonlinear heat sinks (sources), describing radiative cooling in a medium with zero temperature (in a vacuum).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 160-168
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  • 177
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    Heat transfer with nucleate boiling of liquids under weak mass force field conditions (1974)
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    Publication Date: 2011-08-16
    Description: The motion is examined of a vapor bubble growing and rising from a flat horizontal heater in the ideal fluid approximation and taking drag into account. Estimates are given of bubble lifetime, bubble radius at detachment, bubble detachment frequency, and time for the bubble to attain a constant rate of rise. The relations obtained for the microcharacteristics of the boiling process are used to determine the coefficients of heat transfer in developed nucleate boiling. A new form of the equations for describing heat transfer in nucleate boiling in dimensionless parameters is proposed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 131-159
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  • 178
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    Thermocapillary convection in weightless condition (1974)
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    Description: Results are presented of studies on thermocapillary instability of a liquid in a spherical layer with free surface and convection in a rectangular channel with horizontal temperature gradient. It is shown that in vessels partly filled with a viscous incompressible fluid and under essentially weightless conditions free convection may arise due to the surface tension temperature dependence.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 121-130
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  • 179
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    Transient cooling of solid bodies of classical form by radiation (1974)
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    Publication Date: 2011-08-16
    Description: An approximate analytic method is presented for analysis of the unsteady process of radiative cooling of solid bodies of classical form. The nonlinear heat transfer problem is solved by the cascade linearization technique with use of the iteration method. Comparison of the results obtained even in the first approximation with the available numerical solutions indicates adequate engineering accuracy of the proposed technique.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 113-120
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  • 180
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    Thermal regime and temperature stresses in bodies during thermoradiational heating (1974)
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    Publication Date: 2011-08-16
    Description: An approach is developed to the application of the perturbation method for the solution of problems with essential external nonlinearities, based on identification in the boundary condition of a small nonlinear complex which is considered a perturbing function. The solutions obtained in the first approximation with error of 1 to 2% in calculating the unsteady temperature fields are then used to determine the temperature stresses and deformations in solid bodies of classical form.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 88-98
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  • 181
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    Erosion and the gas turbine engine, part 2 (1974)
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    Publication Date: 2011-08-16
    Description: Procedures for protecting aircraft engines from impact damage due to sand and dust particles are discussed. One system is to develop a filtration system to remove most of the solid particles. Another method is to design blade materials and blade protection coatings. The concepts of erosion within aircraft engines are explained. Curves are presented to show the effect of impingement angle on ductile and elastic modes of erosion. Engine sand and dust ingestion tests were conducted on T63-A-5A engines and the results are produced in graph form. The results of tests conducted in a dynamic erosion facility are analyzed.
    Keywords: PROPULSION SYSTEMS
    Type: NBS The Role of Cavitation in Mech. Failures; p 129-145
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  • 182
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    Measurements of hydrogen-helium radiation at shock-layer temperatures appropriate for Jupiter entry. (1973)
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    Publication Date: 2011-08-16
    Description: Shock waves traveling at approximately 16 km/sec into a gas mixture of 7% H2 and 93% He were used to simulate the shock-layer conditions for a representative shallow entry into the Jovian atmosphere. The absolute intensities of line and continuum radiation were measured and the radiative cooling of the shock-heated gas is shown.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 13; Oct. 197
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  • 183
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    Strategy for solar heating and cooling in buildings (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The types of solar energy heating and cooling equipment for use with buildings are discussed. The steps from manufacturing to equipment installation are identified. A feasibility study for the use of solar energy was conducted. The study determined the technical, environmental, economic, sociological, political, and strategic aspects of solar heating and cooling.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: TERRASTAR: Terrest. Appl. of Solar Technol. and Res.; 159 p
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  • 184
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    Market potential for solar heating and cooling in buildings (1973)
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    Publication Date: 2011-08-16
    Description: The use of solar heating and cooling for buildings as a method of conserving fossil fuels is discussed. The residential and commercial end use consumption of energy is tabulated. A survey to project the energy requirements for home and industry heating and cooling is developed. The survey indicates that there is a market potential for solar heating and cooling of buildings. A prediction of three to five billion dollars per year as the potential for solar heating and cooling is made.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: TERRASTAR: Terrest. Appl. of Solar Technol. and Res.; 13 p
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  • 185
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    Thermal shielding by subliming volume reflectors in convective and intense radiative environments. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The behavior of dielectric materials having densely packed internal scattering centers subject to extreme convective and radiative environments is analyzed. Experiments have shown that these materials act as volume reflectors of incident radiation even when the exposed surface is being eroded by thermochemical ablation. The analysis was applied to interpret experiments of subliming Teflon models exposed to combined radiative and convective fluxes up to 1.7 kW/sq cm for several seconds. Results show that, although the exposed surface receded at an apparently steady rate, the internal temperature climbed continually, due to internal absorption of radiation and would have caused failure internally if the test duration were extended a few seconds. Thus, performance is time-limited by the internal absorption coefficient. Results were obtained for larger configurations and other materials. Typically, Teflon shells may withstand radiant fluxes up to 20 kW/sq cm for about 5 sec and fritted quartz up to 50 kW/sq cm for about 8 sec (corresponding to the Jupiter entry).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; July 197
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  • 186
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    Effect of surface catalytic activity on stagnation heat-transfer rates. (1973)
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    Publication Date: 2011-08-16
    Description: An experiment was made to determine the effect heterogeneous catalytic surface reactions have on heat-transfer rates in highly frozen low-density stagnation-point boundary layers. Data were obtained in arc-heated facilities that were capable of producing large percentages of chemical energy frozen in a supersonic freestream. The heat-transfer rate to a silicon-dioxide surface was reduced to a minimum value of only one-third of the value obtained on relatively active nickel and platinum surfaces. This is the result of its low catalytic efficiency. Ionization energy was recovered on both the active and the inactive surfaces, indicating that this energy either was released many times faster than the recombination energy or was not controlled by the surface composition.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; May 1973
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  • 187
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    Interaction of free and forced convection in horizontal tubes in the transition regime. (1973)
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    Publication Date: 2011-08-16
    Description: Experimental investigation of some new aspects of the combined free and forced convection interacting in the transition regime of a horizontal tube under uniform heat flux conditions. The results obtained include indications that thermally induced secondary flows attenuate the fluctuations in low inlet turbulence flows, while they restabilize the flow as the inlet turbulence is increased.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Fluid Mechanics; 57; Feb. 6
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  • 188
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    Stagnation region radiative heating with steady-state ablation during Venus entry. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 10; Feb. 197
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  • 189
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    Lateral expansion of a laser-supported detonation wave in a gas. (1972)
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    Publication Date: 2011-08-16
    Description: A model satisfying the conditions in the burnt (ionized) and ambient undisturbed gases is presented for the two-dimensional case of the absorption wave resulting from the interaction of a laser beam with the plasma it generates in the gas through which the beam propagates. The flowfield of the rarefaction wave resulting from the laser-supported detonation is discussed, along with the computed shock and flow deflection angles.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 10; Dec. 197
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  • 190
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    Electrodynamic sailing - Beating into the solar wind. (1972)
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    Publication Date: 2011-08-16
    Description: The recent suggestion by Alfven (1972) of a novel means of spacecraft propulsion based upon energy extraction from the electromagnetic field of the solar wind is critically reviewed. In response to this review, the original suggestion is somewhat amplified and clarified by its author.
    Keywords: PROPULSION SYSTEMS
    Type: Science; 178; Dec. 8
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  • 191
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    Computed total radiation properties of compressed oxygen between 100 and 1000 K. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 15; Nov. 197
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  • 192
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    Swirling base injection for supersonic combustion ramjets. (1972)
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    Publication Date: 2011-08-16
    Description: Experimental evaluation of the swirling base injection proposed by Swithenbank and Chigier (1969) for application in supersonic combustion ramjets or scramjets. This concept of accelerated mixing in supersonic streams through swirl was tested, but the results indicate that swirl does not produce any enhancement of mixing.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 10; Sept
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  • 193
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    An experimental investigation of radiative properties of aluminum oxide particles. (1972)
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    Publication Date: 2011-08-16
    Description: The radiative properties of aluminum oxide at high temperatures were determined at various wavelengths. Absorption cross-sections of aluminum oxide particles averaged over a particle size distribution were determined by measuring the radiative emission from the particles in a flame and by determining the particle number density and size distribution from measurements of the scattering of laser light incident on the particles in this flame. From these values of average absorption cross-section, the imaginary part of the refractive index was deduced. Results indicate that the absorption cross-section and the imaginary part of the refractive index increase as the temperature increases in the range from 1920 to 2610 K, and that these properties decrease with increasing wavelength in the interval from 0.35 to 1.2 micron, indicating a nongray-body behavior.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 12; Nov. 197
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  • 194
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    Fusion power for space propulsion. (1972)
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    Publication Date: 2011-08-16
    Description: Principles of operation, interplanetary orbit-to-orbit mission capabilities, technical problems, and environmental safeguards are examined for thermonuclear fusion propulsion systems. Two systems examined include (1) a fusion-electric concept in which kinetic energy of charged particles from the plasma is converted into electric power (for accelerating the propellant in an electrostatic thrustor) by the van de Graaf generator principle and (2) the direct fusion rocket in which energetic plasma lost from the reactor has a suitable amount of added propellant to obtain the optimum exhaust velocity. The deuterium-tritium and the deuterium/helium-3 reactions are considered as suitable candidates, and attention is given to problems of cryogenic refrigeration systems, magnet shielding, and high-energy particle extraction and guidance.
    Keywords: PROPULSION SYSTEMS
    Type: New Scientist; 54; Apr. 20
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  • 195
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    Ion-thruster propellant utilization. (1972)
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    Publication Date: 2011-08-16
    Description: Maximum propellant utilization in a mercury electron-bombardment thrustor is evaluated. The primary-electron region in the ion chamber of a bombardment thrustor is analyzed at maximum utilization. Both the analysis and experimental data from a range of ion-chamber configurations show a nearly constant loss rate for un-ionized propellant at maximum utilization over a wide range of total propellant flow rate. The discharge loss level of 1000 eV/ion was used to define maximum utilization. The exact level of this definition has no effect on the qualitative results and little effect on the quantitative results. The results obtained are particularly significant whenever efficient throttled operation is required.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 9; July 197
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  • 196
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    Air film cooling in a nonadiabatic wall conical nozzle. (1972)
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    Publication Date: 2011-08-16
    Description: Experimental data for an air-film cooled conical nozzle operating with a heated-air main stream and a water-cooled wall confirm the validity of Lieu's (1964) method for correlating film cooling data in the accelerated flow of a nonadiabatic-wall nozzle. The film cooling effectiveness modified for nonadiabatic walls by Lieu can be used to correlate film cooling under the condition that the main-stream to coolant velocity ratio at the slot is about 1. Such a ratio provides the optimum cooling effectiveness.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 9; July 197
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  • 197
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    The energy situation (1973)
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    Publication Date: 2011-08-16
    Description: Energy reserves from the principal energy sources other than petroleum and natural gas are summarized. It was found that energy sources are being consumed at rates which exceed the ability to replace them through new discoveries and technology improvements. The costs and implications to environment for using coal and nuclear energy are discussed. Tables are presented on energy consumption, cost of reclamation, and water power capacity.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: The Energy Dilemma and Its Impact on Air Transportation; p 1-48
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  • 198
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    An improved separability approximation for line radiative transport in nonhomogeneous media. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A simple modification to the constant half-width approximation of Wilson and Greif, which is an extension of the well-known Curtis-Godson method to the treatment of temperature variations along the integration path, is introduced which permits a more accurate evaluation of line radiative transport in nonhomogeneous gases. To demonstrate the method's accuracy, comparisons are made with Wilson and Greif and numerical frequency integrated results for the line equivalent width and radiative flux in a planar slab with prescribed Planck function and line half-width spatial variations. These variations are chosen to represent typical shock layer conditions. It is found that the modified procedure reduces the inaccuracies inherent in Wilson and Greif's approximation by factors ranging from 5 to 10, while retaining the latter method's ease of application.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 13; June 197
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  • 199
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    Nonlinear least squares - An aid to thermal property determination. (1973)
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    Publication Date: 2011-08-16
    Description: Nonlinear least squares techniques can be used to determine effective thermal conductivity values from experimental data. Comparisons between measured and predicted conductivity values indicate that the analytically determined values can be used with confidence in performing thermal protection system analyses. A study was performed to compare the relative efficiencies of different minimizing techniques; the method of Peckham was the most efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; May 1973
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  • 200
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    Performance of a modified downstream-cathode MPD thruster. (1973)
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    Publication Date: 2011-08-16
    Description: Discussion of the improvements incorporated since 1969 in a low-power MPD thruster design which is considered a potential candidate for satellite station keeping and attitude control. The improvements include a new cathode design, and changes in thruster geometry, with xenon used as the propellant. A better thermal design is found to be necessary for further improvement of the thruster.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 10; Jan. 197
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