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  • THERMODYNAMICS AND COMBUSTION  (1,363)
  • ddc:330
  • Cell & Developmental Biology
  • 1970-1974  (2,323)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Method of calculating gas dynamics and heat transfer in single stage refrigeration units (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A generalized mathematical model of gas-dynamic and heat transfer processes in single-stage regenerative installations operating in Stirling, MacMahon, Gifford-MacMahon, and pulsating tube cycles is proposed. A numerical method os solving initial equations on a digital computer is given. This makes it possible to calculate the change in the thermodynamic parameters in the working cycle in different machine components, as well as the dependence of cold productivity on the temperature level in the steady regime.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Res. in the Ukraine, No. 3 (NASA-TT-F-15537); p 124-138
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  • 2
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    Nonequilibrium boundary layer at a stagnation point for a hydrogen-helium stream over ablating graphite (1974)
    In:  Other Sources
    Details
    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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  • 3
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    Effect of wall temperature spatial variations on aerodynamic heating to an actively cooled aircraft (1974)
    In:  Other Sources
    Details
    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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  • 4
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    Finite-amplitude thermal convection in a spherical shell (1974)
    In:  Other Sources
    Details
    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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  • 5
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    On the propagation velocity of a detonation-shock combined wave (1974)
    In:  Other Sources
    Details
    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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  • 6
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    Swept-slot film-cooling effectiveness in hypersonic turbulent flow (1974)
    In:  Other Sources
    Details
    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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  • 7
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    Mean flow development and surface heating for an attaching compressible free shear layer (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
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  • 8
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    Evolution of the heat transfer and flow in moderately short turbulent boundary layers in severe pressure gradients (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 17; Sept
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  • 9
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    Aerodynamic heat transfer to RSI tile surfaces and gap intersections (1974)
    In:  Other Sources
    Details
    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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  • 10
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    Nonlinear unsteady contact heat conduction of two-layer shells in the presence of thermal radiation (1974)
    In:  Other Sources
    Details
    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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  • 11
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    Radiative cooling of bodies of arbitrary shape and variable volume in vacuum (1974)
    In:  Other Sources
    Details
    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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  • 12
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    Heat transfer with nucleate boiling of liquids under weak mass force field conditions (1974)
    In:  Other Sources
    Details
    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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  • 13
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    Thermocapillary convection in weightless condition (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    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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  • 14
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    Transient cooling of solid bodies of classical form by radiation (1974)
    In:  Other Sources
    Details
    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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  • 15
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    Thermal regime and temperature stresses in bodies during thermoradiational heating (1974)
    In:  Other Sources
    Details
    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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  • 16
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    Full wave modulator-demodulator amplifier apparatus (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A full-wave modulator-demodulator apparatus is described including an operational amplifier having a first input terminal coupled to a circuit input terminal, and a second input terminal alternately coupled to the circuit input terminal. A circuit is ground by a switching circuit responsive to a phase reference signal and the operational amplifier is alternately switched between a non-inverting mode and an inverting mode. The switching circuit includes three field-effect transistors operatively associated to provide the desired switching function in response to an alternating reference signal of the same frequency as an AC input signal applied to the circuit input terminal.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 17
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    Heat transfer to surface and gaps of RSI tile arrays in turbulent flow at Mach 10.3 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat transfer to gap walls and surface of a simulated reusable surface insulation (RSI) tile array are presented. The data were obtained in the thick, turbulent tunnel wall boundary layer of the Langley Continuous Flow Hypersonic Tunnel at a freestream Mach number of 10.3 and a freestream unit Reynolds number of one million. Pertinent test variables were: (1) tile array orientation (staggered and in-line), (2) gap width, (3) flow angularity, and (4) tile mismatch.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71945
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  • 18
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    Bio-isolated dc operational amplifier (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A bio-isolated dc operational amplifier is described for use in making bioelectrical measurements of a patient while providing isolation of the patient from electrical shocks. The circuit contains a first operational amplifier coupled to the patient with its output coupled in a forward loop through a first optic coupler to a second operational amplifier. The output of the second operational amplifier is coupled to suitable monitoring circuitry via a feedback circuit including a second optic coupler to the input of the first operational amplifier.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 19
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    LC-oscillator with automatic stabilized amplitude via bias current control (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A stable excitation supply for measurement transducers is described. It consists of a single-transistor oscillator with a coil connected to the collector and a capacitor connected from the collector to the emitter. The output of the oscillator is rectified and the rectified signal acts as one input to a differential amplifier; the other input being a reference potential. The output of the amplifier is connected at a point between the emitter of the transistor and ground. When the rectified signal is greater than the reference signal, the differential amplifier produces a signal of polarity to reduce bias current and, consequently, amplification.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 20
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    Comparison of cooling effectiveness of turbine vanes with and without film cooling (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The cooling effectiveness of three film-cooled vanes were compared to the cooling effectiveness of two non-film-cooled vanes. The comparison indicated that, for the vane configurations and test conditions examined, film cooling had an adverse effect near the suction-surface trailing edge of the vanes. Film cooling was found to be beneficial on the pressure surface of the vanes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3022 , E-7860
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  • 21
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    Aerodynamic heating and loading within large open cavities in cone and cone-cylinder-flare models at Mach 6.7 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic heating and loading distributions within large cavities exposed by surface openings to hypersonic flow were determined in the 8-foot high-temperature structures tunnel. Cone and cone-cylinder-flare models with cavities having regular and irregular surface-opening shapes were aerothermally tested at various angles of attack up to 30 deg. Tests were conducted at a Mach number of 6.7, a total temperature of 1800 K, a dynamic pressure of 80 kPa, and a stream unit Reynolds number of 6,000,000 per meter. The results showed that the heating rates at internal reattachment were generally lower but of the same order as the corresponding external heating rates; however, other internal heating rates were an order of magnitude lower. The internal flow showed characteristics of being funneled into jets or being dispersed dependent upon the internal surface contour.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7403 , L-9157
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  • 22
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    Light bulb heat exchanger for magnetohydrodynamic generator applications - Preliminary evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The light-bulb heat-exchanger concept is investigated as a possible means of using a combustion heat source to supply energy to an inert gas MHD power generator system. In this concept, combustion gases flow through a central passage which consists of a duct with transparent walls through which heat is transferred by radiation to a radiation receiver which in turn heats the inert gas by convection. The effects of combustion-gas emissivity, transparent-wall-transmissivity, radiation-receiver emissivity, and the use of fins in the inert gas coolant passage are studied. The results indicate that inert gas outlet temperatures of 2500 K are possible for combustion temperatures of 3200 K and that sufficient energy can be transferred from the combustion gas to reduce its temperature to approximately 2000 K. At this temperature more conventional heat exchangers can be used.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7534 , E-7593
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  • 23
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    An efficiency study on obtaining the minimum weight of a thermal protection system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three minimizing techniques are evaluated to determine the most efficient method for minimizing the weight of a thermal protection system and for reducing computer usage time. The methods used (numerical optimization and nonlinear least squares) for solving the minimum-weight problem involving more than one material and more than one constraint are discussed. In addition, the one material and one constraint problem is discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-58126 , JSC-08678
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  • 24
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    A homogeneous heat pipe design code (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program was developed to facilitate parametric performance evaluation of heat pipes in lightweight heat rejection systems. A description of the code, user's manual, and sample inputs are provided. The emphasis is placed on the analysis and design of homogeneous wick heat pipes. The analysis of the annular heat pipe is included as part of the heat pipe radiator subroutine.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-136831 , JPL-TM-33-663
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  • 25
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    Demodulator for carrier transducers (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A carrier type transducer is supplied with a carrier wave via an audio amplifier, a filter, a frequency divider, and an oscillator. The carrier is modulated in accordance with the parameter being measured by the transducer and is fed to the input of a digital data system which may include a voltmeter. The output of the oscillator and the output of each stage of the divider are fed to an AND or a NAND gate and suitable variable and fixed delay circuits to the command input of the digital data system. With this arrangement, the digital data system is commanded to sample at the proper time so that the average voltage of the modulated carrier is measured. It may be utilized with ancillary circuitry for control of the parameter
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 26
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    System for stabilizing cable phase delay utilizing a coaxial cable under pressure (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Stabilizing the phase delay of signals passing through a pressurizable coaxial cable is disclosed. Signals from an appropriate source at a selected frequency, e.g., 100 MHz, are sent through the controlled cable from a first cable end to a second cable end which, electrically, is open or heavily mismatched at 100 MHz, thereby reflecting 100 MHz signals back to the first cable end. Thereat, the phase difference between the reflected-back signals and the signals from the source is detected by a phase detector. The output of the latter is used to control the flow of gas to or from the cable, thereby controlling the cable pressure, which in turn affects the cable phase delay.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 27
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    Effects of pressure, oxygen concentration, and forced convection on flame spread rate of Plexiglas, Nylon and Teflon (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments were conducted in which the burning of cylindrical materials in a flowing oxidant stream was studied. Plexiglas, Nylon, and Teflon fuel specimens were oriented such that the flames spread along the surface in a direction opposed to flowing gas. Correlations of flame spread rate were obtained that were power law relations in terms of pressure, oxygen concentration, and gas velocity.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7555 , E-7611
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  • 28
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    Film cooling in a combustor operating at fuel-rich exit conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data were taken with a film-cooled test plate placed in the exhaust stream of a rectangular combustor. Results showed that in a fuel-rich zone, fuel entrained into the film-cooling air would burn at the conditions tested. Test conditions were cooling-gas flow rates, 9.5 and 5 percent of total gas flow; cooling-gas velocities, 23 and 12 m/sec; ambient-temperature cooling gas; hot-gas velocity, nominally 215 m/sec; fuel-air ratio to stoichiometric fuel-air ratio values of 0.1, 0.8, 1.0, 1.2, and 1.35, resulting in hot-gas temperatures from 590 to 2100 K; and atmospheric pressure. Analytical prediction of wall temperatures agreed reasonably well with experimental results.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7513 , E-7561
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  • 29
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    Liquefaction dynamics of n-octadecane in cylindrical coordinates (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The study presents one method of mathematically modeling the effects of gravity-induced free convection upon the melting phenomena of a finite paraffin slab. The theoretical model is based on the numerical computer solution of the solid phase and liquid phase energy equations, coupled with an imposed ideal-viscous flow approximation. An implicit alternating-direction technique is used as the finite-difference approximation for the basic energy equations in the numerical solution. The theoretical predictions are compared to experimental data from an annular test cell, in which n-octadecane, C18H38, was used as the test material. The results show that the model is a good first approximation to the solution of solid-liquid phase change involving gravity-induced free convection.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
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  • 30
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    Unsteady temperature distribution in volume reflectors (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The development of unsteady temperature distributions in semitransparent scattering materials under the influence of arbitrary incident radiative flux with other than specified temperature boundary conditions is considered. Specifically, such a problem is considered for an approximate radiative transfer model which allows analytic solutions. The model represents the unsteady, one-dimensional, radiative heating of a weakly absorbing, semitransparent medium with specified conductive heat flux at one boundary. The radiation field is modeled using an approximation to the radiative heat flux obtained by solution of the Kubelka-Munk differential equations.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 12; May 1974
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  • 31
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    Capacitance multiplier and filter synthesizing network (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A circuit using a differential amplifier multiplies the capacitance of a discrete interating capacitor by (r sub 1 + R sub 2)/R sub 2, where R sub 1 and R sub 2 are values of discrete resistor coupling an input signal e sub 1 of the amplifier inputs. The output e sub 0 of the amplifier is fed back and added to the signal coupled by the resistor R sub 2 to the amplifier through a resistor of value R sub 1. A discrete resistor R sub x may be connected in series for a lag filter, and a discrete resistor may be connected in series with the capacitor for a lead-lag filter. Voltage dividing resistors R sub a and R sub b may be included in the feedback circuit of the amplifier output e sub o to independently adjust the circuit gain e sub i/e sub o.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 32
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    Development of electrical feedback controlled heat pipes and the advanced thermal control flight experiment (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development and characteristics of electrical feedback controlled heat pipes (FCHP) are discussed. An analytical model was produced to describe the performance of the FCHP under steady state and transient conditions. An advanced thermal control flight experiment was designed to demonstrate the performance of the thermal control component in a space environment. The thermal control equipment was evaluated on the ATS-F satellite to provide performance data for the components and to act as a thermal control system which can be used to provide temperature stability of spacecraft components in future applications.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-114751 , DTM-74-2
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  • 33
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    Viscosity and thermal conductivity coefficients of gaseous and liquid oxygen (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equations and tables are presented for the viscosity and thermal conductivity coefficients of gaseous and liquid oxygen at temperatures between 80 K and 400 K for pressures up to 200 atm. and at temperatures between 80 K and 2000 K for the dilute gas. A description of the anomalous behavior of the thermal conductivity in the critical region is included. The tabulated coefficients are reliable to within about 15% except for a region in the immediate vicinity of the critical point. Some possibilities for future improvements of this reliability are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-2440
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  • 34
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    Analysis of combustion instability in liquid propellant engines with or without acoustic cavities (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical studies have been made of the relative combustion stability of various propellant combinations when used with hardware configurations representative of current design practices and with or without acoustic cavities. Two combustion instability models, a Priem-type model and a modification of the Northern Research and Engineering (NREC) instability model, were used to predict the variation in engine stability with changes in operating conditions, hardware characteristics or propellant combination, exclusive of acoustic cavity effects. The NREC model was developed for turbojet engines but is applicable to liquid propellant engines. A steady-state combustion model was used to predict the needed input for the instability models. In addition, preliminary development was completed on a new model to predict the influence of an acoustic cavity with specific allowance for the effects the nozzle, steady flow and combustion.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134387 , R-9353
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    Studies of heat source driven natural convection (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Natural convection energy transport in a horizontal layer of internally heated fluid with a zero heat flux lower boundary, and an isothermal upper boundary, has been studied. Quantitative information on the time-mean temperature distribution and the fluctuating component of temperature about the mean temperature in steady turbulent convection are obtained from a small thermocouple inserted into the layer through the upper bounding plate. Data are also presented on the development of temperature at several vertical positions when the layer is subject to both a sudden increase and to a sudden decrease in power input. For changes of power input from zero to a value corresponding to a Rayleigh number much greater than the critical linear stability theory value, a slight hysteresis in temperature profiles near the upper boundary is observed between the heat-up and cool-down modes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-70232 , TR-3746-1
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  • 36
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    Digital servo controller (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A system, for generating a signal to control the rotation of a shaft supporting an antenna so that the antenna is rotated the shortest angular distance from a present angular position to a new desired angular position, was described. The system comprises a shaft encoder which generates a digital encoder signal indicating the present position of the shaft. A command signal is compared with the encoder signal to produce an analog signal for rotating the antenna. An error signal is produced for controlling the direction of rotation of the antenna.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    Radiative property investigation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed formulation of radiative heat transfer problems involving the use of bidirectional reflectance is discussed. Except for very simple systems this formulation is very intricate. For this reason and the fact that bidirectional data are scarce, such a formulation is not in common use. However, with the development of the digital computer there have been numerical methods developed for detailed radiative investigations using the bidirectional reflectance. Since computations using bidirectional reflectance are coming into use for spacecraft radiative studies, it is necessary to have reflectance data on the materials involved. Materials that are frequently studied are coatings which are used in controlling the thermal environment of spacecrafts. This study is primarily concerned with the bidirectional reflectance of zinc oxide which is one constituent commonly used for coatings.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-138459
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  • 38
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    Thermodynamic analysis of an axial-flow laser-powered thruster (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A one-dimensional model of a laser-powered thruster is analyzed. The model consists of two flow regions: a laser-heated region and a coaxial region outside the laser region. Different bulk velocities and temperatures are assigned for each region, and a common pressure is assigned for both regions. The one-dimensional inviscid flow equations are solved for each region with the same initial conditions. The results indicate that in order to prevent choked flow while increasing the anthalpy of the inlet gas by a factor of 10, the initial Mach number must be less than 0.14. For hydrogen gas seeded with 10 percent tungsten and entering the thruster tube at 10 atm and 300 K and a laser beam one-half the area of the tube, a tube length between 20 and 50 cm is required to vaporize the particles.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3077 , E-7891
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  • 39
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    Differential phase shift keyed signal resolver (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A differential phase shift keyed signal resolver resolves the differential phase shift in the incoming signal to determine the data content thereof overcoming phase uncertainty without requiring a transmitted reference signal.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 40
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    Electric field measuring and display system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An apparatus is described for monitoring the electric fields of cloud formations within a particular area. It utilizes capacitor plates that are alternately shielded from the clouds for generating an alternating signal corresponding to the intensity of the electric field of the clouds. A synchronizing signal is produced for controlling sampling of the alternating signal. Such samplings are fed through a filter and converted by an analogue to digital converter into digital form and subsequently fed to a transmitter for transmission to the control station for recording.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 41
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    Effect of primary-zone equivalence ratio and hydrogen addition on exhaust emission in a hydrocarbon-fueled combustor (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of reducing the primary-zone equivalence ratio on the exhaust emission levels of oxides of nitrogen, carbon monoxide, and unburned hydrocarbons in experimental hydrocarbon-fueled combustor segments at simulated supersonic cruise and idle conditions were investigated. In addition, the effects of the injection of hydrogen fuel (up to 4 percent of the total weight of fuel) on the stability of the hydrocarbon flame and exhaust emissions were studied and compared with results obtained without hydrogen addition.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3117 , E-8011
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  • 42
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    A cascade investigation of a convection- and film-cooled turbine vane made from radially stacked laminates (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat-transfer was investigated on an air-cooled turbine vane made from photoetched laminates that were joined by diffusion bonding. Data from the investigation were compared with data of an impingement-, convection-, and film-cooled vane and a full-coverage film-cooled vane, and data of a transpiration-cooled vane.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3122 , E-8002
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  • 43
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    Development of a second order closure model for computation of turbulent diffusion flames (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A typical eddy box model for the second-order closure of turbulent, multispecies, reacting flows developed. The model structure was quite general and was valid for an arbitrary number of species. For the case of a reaction involving three species, the nine model parameters were determined from equations for nine independent first- and second-order correlations. The model enabled calculation of any higher-order correlation involving mass fractions, temperatures, and reaction rates in terms of first- and second-order correlations. Model predictions for the reaction rate were in very good agreement with exact solutions of the reaction rate equations for a number of assumed flow distributions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132524 , ARAP-222
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  • 44
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    Integrated P-channel MOS gyrator (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A gyrator circuit is described which is of the conventional configuration of two amplifiers in a circular loop, one producing zero phase shift and the other producing 180 phase reversal, in a circuit having medium Q composed of all field effect transistors of the same conductivity type. The current source to each gyrator amplifier comprises an amplifier which responds to changes in current, with the amplified signals feed back so as to limit current. The feedback amplifier has a large capacitor connected to bypass high frequency components, thereby stabilizing the output. The design makes possible fabrication of circuits with transistors of only one conductivity type, providing economies in manufacture and use.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 45
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    Lateral conduction effects on heat-transfer data obtained with the phase-change paint technique (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computerized tool, CAPE, (Conduction Analysis Program using Eigenvalues) has been developed to account for lateral heat conduction in wind tunnel models in the data reduction of the phase-change paint technique. The tool also accounts for the effects of finite thickness (thin wings) and surface curvature. A special reduction procedure using just one time of melt is also possible on leading edges. A novel iterative numerical scheme was used, with discretized spatial coordinates but analytic integration in time, to solve the inverse conduction problem involved in the data reduction. A yes-no chart is provided which tells the test engineer when various corrections are large enough so that CAPE should be used. The accuracy of the phase-change paint technique in the presence of finite thickness and lateral conduction is also investigated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-2435
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  • 46
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    Curve fits of predicted inviscid stagnation-point radiative heating rates, cooling factors, and shock standoff distances for hyperbolic earth entry (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Curve-fit formulas are presented for the stagnation-point radiative heating rate, cooling factor, and shock standoff distance for inviscid flow over blunt bodies at conditions corresponding to high-speed earth entry. The data which were curve fitted were calculated by using a technique which utilizes a one-strip integral method and a detailed nongray radiation model to generate a radiatively coupled flow-field solution for air in chemical and local thermodynamic equilibrium. The range of free-stream parameters considered were altitudes from about 55 to 70 km and velocities from about 11 to 16 km.sec. Spherical bodies with nose radii from 30 to 450 cm and elliptical bodies with major-to-minor axis ratios of 2, 4, and 6 were treated. Powerlaw formulas are proposed and a least-squares logarithmic fit is used to evaluate the constants. It is shown that the data can be described in this manner with an average deviation of about 3 percent (or less) and a maximum deviation of about 10 percent (or less). The curve-fit formulas provide an effective and economic means for making preliminary design studies for situations involving high-speed earth entry.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7622 , L-9315
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  • 47
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    The effect of temperature induced surface tension gradients on bubble mechanics (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Experiments were conducted to examine in detail the influence of surface tension gradient induced flow, the Marangoni effect. One set of studies provided visual results that demonstrated the occurrence and magnitude of the Marangoni effect. Another portion of the work was directed to bubble force measurements. These studies used in deflection of a very fine cantilevered wire with an attached bubble as a means of measuring force with and without temperature gradients. The experimental force data were found to check existing theoretical predictions reasonably well except for the case where the test fluid had a sizeable vapor pressure. In this situation the thermophoretic force on the bubble was much higher than predicted.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Applied Sctientific Research; 29; June 197
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  • 48
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    Time-resolved spectra of bulk titanium combustion (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Some preliminary spectroscopic results of an investigation of the radiation from bulk specimens of burning titanium are presented. The use of larger stationary specimens is shown to have considerably eased some of the experimental difficulties associated with metal combustion research and to approximate more closely the conditions prevailing in large-scale accidental metal fires.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Combustion and Flame; 23; Aug. 197
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  • 49
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    Stability of partially lined combustors with distributed combustion (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An integral method for theoretical evaluation of the stability of confined flows with mass sources is presented. This method is applied to evaluate the effect of partial length acoustic liners on liquid propellant combustors with distributed combustion sources. The combustor is modeled as a right circular cylinder terminated by a multiorifice (constant Mach number) nozzle. The spatial spread of combustion in the chamber is represented by an arbitrary number of pressure sensitive planar mass sources. On the cylindrical periphery of the chamber is an acoustic absorber of arbitrary length, position, and damping capability. Integral equations are developed from the partial differential equations describing the nonsteady flow and are solved iteratively. Results are given in terms of linear neutral stability plots using a pressure sensitive combustion response. Calculations indicate that increasing the axial spread of combustion increases the stability of the combustor and the effectiveness of the absorber. The most effective linear placement appears at the location of greatest combustion concentration.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 12; Apr. 197
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  • 50
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    Thermodynamic properties derived from the free volume model of liquids (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An equation of state and expressions for the isothermal compressibility, thermal expansion coefficient, heat capacity, and entropy of liquids have been derived from the free volume model partition function suggested by Turnbull. The simple definition of the free volume is used, and it is assumed that the specific volume is directly related to the cube of the intermolecular separation by a proportionality factor which is found to be a function of temperature and pressure as well as specific volume. When values of the proportionality factor are calculated from experimental data for real liquids, it is found to be approximately constant over ranges of temperature and pressure which correspond to the dense liquid phase. This result provides a single-parameter method for calculating dense liquid thermodynamic properties and is consistent with the fact that the free volume model is designed to describe liquids near the solidification point.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Metallurgical Transactions; 5; Mar. 197
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  • 51
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    Experimental determination of turbulence in a GH2-GOX rocket combustion chamber (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The intensity of turbulence and the Lagrangian correlation coefficient for a gaseous rocket combustion chamber have been determined from the experimental measurements of the tracer gas diffusion. A combination of Taylor's turbulent diffusion theory and Spalding's numerical method for solving the conservation equations of fluid mechanics was used to calculate these quantities. Taylor's theory was extended to consider the inhomogeneity of the turbulence field in the axial direction of the combustion chamber. An exponential function was used to represent the Lagrangian correlation coefficient. The results indicate that the maximum value of the intensity of turbulence is about 15% and the Lagrangian correlation coefficient drops to about 0.12 in one inch of the chamber length.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134672
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  • 52
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    Pulse stretcher for narrow pulses (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A pulse stretcher for narrow pulses is presented. The stretcher is composed of an analog section for processing each arriving analog pulse and a digital section with logic for providing command signals to the gates and switches in the analog section.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 53
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    Techniques for aerothermal tests of large, flightweight thermal protection panels in a Mach 7 wind tunnel (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Thermal performance and structural integrity are experimentally evaluated in the Langley 8-ft high temperature structures tunnel, which uses a combustion products test medium to provide realistic combinations of aerodynamic heating and loading. Recently developed techniques provide independent control of rate and magnitude of surface heating and differential pressure, protection against adverse acoustics buffeting during facility starting and stopping, programed radiant heating before exposing test panels to the high energy stream, and infrared radiometry for detailed surface temperatures. These techniques were verified repeatedly by return of useful data on metallic and nonmetallic panel concepts of reusable surface insulation.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71983 , L-9477
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  • 54
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    Similarity constraints in testing of cooled engine parts (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study is made of the effect of testing cooled parts of current and advanced gas turbine engines at the reduced temperature and pressure conditions which maintain similarity with the engine environment. Some of the problems facing the experimentalist in evaluating heat transfer and aerodynamic performance when hardware is tested at conditions other than the actual engine environment are considered. Low temperature and pressure test environments can simulate the performance of actual size prototype engine hardware within the tolerance of experimental accuracy if appropriate similarity conditions are satisfied. Failure to adhere to these similarity constraints because of test facility limitations or other reasons, can result in a number of serious errors in projecting the performance of test hardware to engine conditions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7707
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  • 55
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    Load insensitive electrical device (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A class of power converters is described for supplying direct current at one voltage from a source at another voltage. It includes a simple passive circuit arrangement of solid-state switches, inductors, and capacitors by which the output voltage of the converter tends to remain constant in spite of changes in load. The switches are sensitive to the current flowing in the circuit and are employed to permit the charging of capacitance devices in accordance with the load requirements. Because solid-state switches (such as SCR's) may be used with relatively high voltage and because of the inherent efficiency of the invention that permits relatively high switching frequencies, power supplies built in accordance with the invention, together with their associated cabling, can be substantially lighter in weight for a given output power level and efficiency of operation than systems of the prior art.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 56
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    Explosive propulsion applications (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility and application of an explosive propulsion concept capable of supporting future unmanned missions in the post-1980 era were examined and recommendations made for advanced technology development tasks. The Venus large lander mission was selected as the first in which the explosive propulsion concept can find application. A conceptual design was generated and its performance, weight, costs, and interaction effects determined. Comparisons were made with conventional propulsion alternatives. The feasibility of the explosive propulsion system was verified for planetology experiments within the dense atmosphere of Venus as well as the outer planets. Additionally, it was determined that the Venus large lander mission could be augmented ballistically with a significant delivery margin.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-138454 , JPL-TM-33-675
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  • 57
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    An experimental investigation of jet plume simulation with solid circular cylinders (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted in the Langley 16-foot transonic tunnel to determine the effectiveness of utilizing solid circular cylinders to simulate the jet exhaust plume for a series of four isolated circular arc afterbodies with little or no flow separation. This investigation was conducted at Mach numbers from 0.40 to 1.30 at 0 deg angle of attack. Plume simulators with simulator diameter to nozzle exit diameter ratios of 0.82, 0.88, 0.98, and 1.00 were investigated with one of the four configurations while the 0.82 and 1.00 simulators were investigated with the other three. Reynolds number based on maximum model diameter varied from approximately 1.50 to 2.14 million.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71963
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  • 58
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    Effect of diffuser bleed on performance of an annular swirl can combustor (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A full-scale annular swirl can combustor equipped with diffuser bleed capability was tested at low fuel-air ratio, burning natural gas fuel. Test results show that, by drawing off a small amount of air on the inner or outer diffuser wall, the radial profile of combustor exit temperature could be changed from a strongly tip biased, to a strongly hub biased shape. Furthermore, combustor total pressure loss could be reduced by about one third by using a total bleed rate equal to 6 percent of diffuser inlet flow. At simulated engine idle conditions combustion efficiency was increased from 64 percent to nearly 100 percent by using 3 percent outer wall bleed. Combustor blowout performance was also improved significantly by using this diffuser bleed scheme.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3056 , E-7854
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    Performance of LI-1542 reusable surface insulation system in a hypersonic stream (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermal and structural performance of a large panel of LI-1542 reusable surface insulation tiles was determined by a series of cyclic heating tests using radiant lamps and aerothemal tests in the Langley 8-foot high-temperature structures tunnel. Aerothermal tests were conducted at a free-stream Mach number of 6.6, a total temperature of 1830 K, Reynolds numbers of 2.0 and 4,900,000 per meter, and dynamic pressures of 29 and 65 kPa. The results suggest that pressure gradients in gaps and flow impingement on the header walls at the end of longitudinal gaps are sources for increased gap heating. Temperatures higher than surface radiation equilibrium temperature were measured deep in gaps and at the header walls. Also, the damage tolerance of the LI-1542 tiles appears to be very high. Tile edge erosion rate was slow; could not be tolerated in a shuttle application. Tiles soaked with water and subjected to rapid depressurization and aerodynamic heating showed no visible evidence of damage.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71955
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  • 60
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    Burning of solids in oxygen-rich environments in normal and reduced gravity (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental program was conducted to investigate the combustion characteristics of solids burning in a weightless environment. The combustion characteristics of thin cellulose acetate material were obtained from specimens burned in supercritical as well as in low pressure oxygen atmospheres. Flame spread rates were measured and found to depend on material thickness and pressure in both normal gravity (1-g) and reduced gravity (0-g). A gravity effect on the burning process was also observed; the ratio of 1-g to 0-g flame spread rate becomes larger with increasing material thickness. Qualitative results on the combustion characteristics of metal screens (stainless steel, Inconel, copper, and aluminum) burning in supercritical oxygen and normal gravity are also presented. Stainless steel (300 sq mesh) was successfully ignited in reduced gravity; no apparent difference in the flame spread pattern was observed between 1-g and 0-g.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3055 , E-7848
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  • 61
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    Rotary solenoid shutter drive assembly and rotary inertia damper and stop plate assembly (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A camera shutter assembly composed of a pair of superposed opaque planar shutter blades, each having an aperture and being arranged for reciprocal linear movement is disclosed. A pair of rotary solenoids, each connected to one of the blades by a linkage and arranged to be actuated separately at a predetermined interval is provided. An inertia damper and stop plate is built into each solenoid to prevent rebound.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 62
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    Ultra-stable oscillator with complementary transistors (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A high frequency oscillator, having both good short and long term stability, is formed by including a piezoelectric crystal in the base circuit of a first bi-polar transistor circuit, the bi-polar transistor itself operated below its transitional frequency and having its emitter load chosen so that the input impedance, looking into the base thereof, exhibits a negative resistance in parallel with a capacitive reactance. Combined with this basic circuit is an auxiliary, complementary, second bi-polar transistor circuit of the same form with the piezoelectric crystal being common to both circuits. By this configuration small changes in quiescent current are substantially cancelled by opposite variations in the second bi-polar transistor circuit, thereby achieving from the oscillator a signal having its frequency of oscillation stable over long time periods as well as short time periods.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 63
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    Amplitude steered array (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A spin stabilized satellite has an electronically despun antenna array comprising a multiplicity of peripheral antenna elements. A high gain energy beam is established by connecting a suitable fraction or array of the elements in phase. The beam is steered or caused to scan by switching elements in sequence into one end of the array as elements at the other end of the array are switched out. The switching transients normally associated with such steering are avoided by an amplitude control system. Instead of abruptly switching from one element to the next, a fixed value of power is gradually transferred from the element at the trailing edge of the array to the element next to the leading edge.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    Rapidly pulsed, high intensity, incoherent light source (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A rapid pulsing, high intensity, incoherent light is produced by selectively energizing a plurality of discharge lamps with a triggering circuit. Each lamp is connected to a capacitor, and a power supply is electrically connected to all but one of the capacitors. This last named capacitor is electrically connected to a discharge lamp which is connected to the triggering circuit.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 65
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    Effect of geometrical and flow parameters on high-effectiveness region of film cooling (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Previous analyses for an inviscid jet injected into a stream and the turbulent mixing region which forms between jet and stream are used to find the extent of the core region in a cooling film by calculating the growth of the turbulent boundary layer on the downstream wall. The core is a region of nearly perfect effectiveness which ends at the intersection of the boundary layer and the mixing region. The calculations show that the most important geometrical factor bearing on the length of the core is the curvature of the wall. When the radius of curvature is large, the boundary layer remains thin and the core is long. The effects of Reynolds number, total-pressure difference between film and stream, and lateral position of the downstream wall are also investigated. The step configuration is shown to have a longer core than the slot for the same flow conditions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7636 , E-7538
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    Jet engine exhaust emissions of high altitude commercial aircraft projected to 1990 (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Projected minimum levels of engine exhaust emissions that may be practicably achievable for future commercial aircraft operating at high-altitude cruise conditions are presented. The forecasts are based on:(1) current knowledge of emission characteristics of combustors and augmentors; (2) the status of combustion research in emission reduction technology; and (3) predictable trends in combustion systems and operating conditions as required for projected engine designs that are candidates for advanced subsonic or supersonic commercial aircraft fueled by either JP fuel, liquefied natural gas, or hydrogen. Results are presented for cruise conditions in terms of both an emission index (g constituent/kg fuel) and an emission rate (g constituent/hr).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3007 , E-7822
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  • 67
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    Experimental transient vane temperatures in a cascade for gas stream temperature cycling between 922 and 1644 K (1200 and 2500 F) (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Experimental transient turbine vane metal temperatures were obtained from tests conducted on air-cooled vanes installed in a four-vane cascade for a gas temperature cycled between 922 and 1644 K (1200 and 2500 F). Transient data were recorded by a high-speed data acquisition system. Temperatures at the same phase of each transient cycle were repeatable between cycles to within 11 kelvins (20 F), simulated cruise and idle steady-state readings were repeated by the cruise and idle readings taken from the ends of a transient half-cycle at low pressure to within 17 kelvins (30 F). The tests were conducted at pressure levels of 31 and 83 N-sq cm (45 and 120 psia) with coolant temperatures of 811 and 589 K (1000 and 600 F), respectively.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3005 , E-7755
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  • 68
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    An adverse effect of film cooling on the suction surface of a turbine vane (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Film-cooling-air ejection from the suction surface of a turbine vane was investigated. This investigation was conducted in a four-vane cascade on a J75 size turbine vane which had a row of holes near the leading edge. The experimental data are presented. It was found that a small amount of film-cooling air has a detrimental effect on the downstream vane wall cooling effectiveness. It was also shown that the presence of the film-cooling holes, without blowing, also cause an increase in vane wall temperatures. These results came from an increase in the gas-side heat transfer coefficient that was apparently caused by a laminar or transitional boundary layer becoming transitional or turbulent.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7618 , E-7744
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  • 69
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    Metal-wool heat shields for space shuttle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The packaging of metal wool for reusable thermal heat shields applied to aerodynamic and other surfaces for the space shuttle was analyzed and designed, and samples were fabricated and experimentally studied. Parametric trends were prepared for selected configurations. An all-metal thermally efficient, reliable, reusable and producible heat shield system was designed and structurally tested for use on spacecraft aerodynamic surfaces where temperatures do not exceed 810 K. Stainless steel sheet, primarily for structure and secondarily in the transverse plane for thermal expansion, was shown to accommodate thermal expansion in all directions when restrained at the edges and heated to 1360 K. Aerodynamic loads of 0.35 x 1000,000 newtons/sq meter, and higher, may be easily accepted by structures of this design. Seven all-metal thermal protection specimens, 12.7 cm square and 2.5 cm thick were fabricated and are being experimentally evaluated at simulated shuttle entry conditions in an arc jet facility.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132389
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  • 70
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    Crossflow effects on impingement cooling of a turbine vane (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An air-cooled turbine vane was tested in a four-vane cascade. Heat transfer characteristics of the impingement cooled midchord region are reported. Experimental Nusselt numbers of six midchord locations are examined for the effect of crossflow and compared to those predicted by impingement correlations found in the literature.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3029 , E-7768
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  • 71
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    An exact solution of a simplified two-phase plume model (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An exact solution of a simplified two-phase, gas-particle, rocket exhaust plume model is presented. It may be used to make the upper-bound estimation of the heat flux and pressure loads due to particle impingement on the objects existing in the rocket exhaust plume. By including the correction factors to be determined experimentally, the present technique will provide realistic data concerning the heat and aerodynamic loads on these objects for design purposes. Excellent agreement in trend between the best available computer solution and the present exact solution is shown.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Southeastern Conference on Theoretical and Applied Mechanics; Mar 21, 1974 - Mar 22, 1974; Washington, DC
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  • 72
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    Cryogenic and low temperature heat pipe/cooler studies for spacecraft application (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The prime purpose of the present work is to examine cryogenic heat pipe/cooler feasibility in the 80 to 100 K temperature range and in the regimes of operation required for NASA spacecraft. Present requirements within these regimes are (1) cooling load of less than 1 to 2 watt per cooler, (2) small detector/heat pipe interface area, and (3) high system reliability and long lifetime operations. The cooling capacity of practical radiant coolers is very low in this temperature range, and very temperature sensitive. Detector performance is also strongly dependent on temperatures in this regime. It is, therefore important to understand the interplay of the heat pipe and its effects on overall system performance.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-753 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 73
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    Heat Transfer and Fluid Mechanics Institute, 24th, Oregon State University, Corvallis, Ore., June 12-14, 1974, Proceedings (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Recent theoretical and experimental studies in heat transfer and fluid mechanics, including some environmental protection investigations, are presented in a number of papers. Some of the topics covered include condensation heat transfer, a model of turbulent momentum and heat transfer at points of separation and reattachment, an explicit scheme for calculations of confined turbulent flows with heat transfer, heat transfer effects on a delta wing in subsonic flow, fluid mechanics of ocean outfalls, thermal plumes from industrial cooling water, a photochemical air pollution model for the Los Angeles air basin, and a turbulence model of diurnal variations in the planetary boundary layer. Individual items are announced in this issue.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Heat Transfer and Fluid Mechanics Institute; Jun 12, 1974 - Jun 14, 1974; Corvallis, OR; US
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  • 74
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    An approximate inviscid radiating flow-field analysis for sphere-cone Venusian entry vehicles (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A computational method based on the earlier work of one of the authors has been improved and modified to provide an accurate and rapid prediction of the radiating flow about blunt conical probes entering the atmosphere of Venus. Special features include a more general approximate equation of state, a more rapidly converging iteration scheme, a 38-step absorption coefficient model for a Venus atmosphere gas mixture model, and a shock-shape formula which yields a computed body shape in excellent agreement with the desired body. The method was used to calculate distributions of radiative heating for a large spherically blunted conical probe vehicle (1.219 m base diameter) and for three small spherically blunted conical probe vehicles (0.724 m base diameter). Solutions obtained with the presently developed approximate method required short computing times of the order of 1 to 3 minutes for each complete solution and gave agreements of 10% to 15% with the more exact predictions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-758 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 75
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    Volume reflecting heat shields for entry into the giant planet atmospheres (1974)
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    Publication Date: 2019-07-13
    Description: The performance of a volume reflecting or backscattering silica heat shield is examined for an entry probe into the severe radiative environments of Saturn, Uranus, and Jupiter. The governing equations for the material response are solved numerically and include the effects of temperature-dependent thermal properties, temperature- and wavelength-dependent radiative properties, and surface recession caused by thermochemical ablation. The influence of the scattering properties on backface temperature is examined, and results are presented which show the required heat-shield thickness for the entry trajectories selected.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-669 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 76
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    Temperature difference-dependent interface thermal resistance of ring-stiffened, corrugated spacecraft shrouds (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-729 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 77
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    Parametric performance of extruded axial grooved heat pipes from 100 to 300 K (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Extensive performance data derived from tests with an aluminum axial grooved extruded heat pipe is presented for oxygen, methane, ethane, and ammonia as working fluids. The effects of operating temperature, fluid inventory, heat flux, and elevation on the transport capability and the evaporator and condenser film coefficients are measured and compared to theory. The data correlation indicates that, in addition to the viscous pressure drop of the fluid, a vapor induced liquid pressure drop must be taken into account at temperatures near or below the normal boiling point of the fluid. Methane, ethane, and ammonia are all suitable working fluids for this groove geometry; however, oxygen, because of its low static height, is at best marginal in the 100-120 K range.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-724 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 78
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    Predicting spacecraft multilayer insulation performance from heat transfer measurements (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Multilayer insulation (MLI) ideally consists of a series of radiation shields with low-conductivity spacers. When MLI blankets were installed on cryogenic tanks or spacecraft, a large discrepancy between the calorimeter measurements and the performance of the installed blankets was discovered. It was found that discontinuities such as exposed edges coupled with high lateral heat transfer created 'heat leaks' which overshadowed the basic heat transfer of the insulation. Approaches leading to improved performance predictions of MLI units are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Symposium on Heat transmission measurements in thermal insulations; Apr 16, 1973 - Apr 17, 1973; Philadelphia, PA
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  • 79
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    Advanced Rankine and Brayton cycle power systems - Materials needs and opportunities (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Conceptual advanced potassium Rankine and closed Brayton power conversion cycles offer the potential for improved efficiency over steam systems through higher operating temperatures. However, for utility service of at least 100,000 hours, materials technology advances will be needed for such high temperature systems. Improved alloys and surface protection must be developed and demonstrated to resist coal combustion gases as well as potassium corrosion or helium surface degradation at high temperatures. Extensions in fabrication technology are necessary to produce large components of high temperature alloys. Long-time property data must be obtained under environments of interest to assure high component reliability.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Materials for Power Systems Meeting; Jun 17, 1974 - Jun 19, 1974; Seven Springs, PA
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  • 80
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    Thermal conductivity of evacuated glass beads - Line source measurements in a large volume bead bed between 225 and 300 K (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Symposium on Heat transmission measurements in thermal insulations; Apr 16, 1973 - Apr 17, 1973; Philadelphia, PA
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  • 81
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    Radiative contribution to the thermal conductivity of fibrous insulations (1974)
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    Publication Date: 2019-07-13
    Description: An approach is shown for using a simple two-flux model to interpret infrared transmission data for a variety of reuseable surface insulations materials and to calculate the radiation transmission. A description is given of preliminary experiments on mullite and silica-based materials. The calculated parameters are compared with the measured values of the total thermal conductivity, as determined on guarded hot plate equipment. It is pointed out that for many samples the newly developed four-flux model must be utilized because the scattering properties of the fibers are often dependent on the wavelength of the radiation.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Symposium on Heat transmission measurements in thermal insulations; Apr 16, 1973 - Apr 17, 1973; Philadelphia, PA
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  • 82
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    Shock tube measurements of specific reaction rates in the branched chain CH4-CO-O2 system (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Rate constants of two elementary bimolecular reactions involved in the oxidation of methane have been determined by monitoring the exponential growth of CO flame band emission behind incident shocks in three suitably chosen gas mixtures. The data do not support a mechanism which invokes the four center process CH3 + O2 yields CH2O + OH for the reaction of methyl with oxygen.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Symposium on Combustion; Aug 25, 1974 - Aug 31, 1974; Tokyo; Japan
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  • 83
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    Development of a blocking orifice thermal diode heat pipe (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new geometry is described for low temperature diode heat pipes employing excess liquid to block the vapor space of the evaporator and part of the transport section during reverse mode conditions. An orifice plate is placed in the pipe at the blocking meniscus location, with the opening arranged to permit proper liquid distribution in both ground tests and zero 'g' operation. Parametric analytical results are presented for several fluids (carbon tetrafluoride, methane, and ethane). Experimental data is presented for a room temperature diode verifying feasibility, and a 1/4 in. O.D. cryogenic diode with methane working fluid.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-754 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 84
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    Diffusive ignition and combustion in a wall jet (1974)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Hydrogen is injected from a downstream facing step in a wall into a high-temperature stream. Temperature and hydroxyl radical concentration are measured downstream of the injection plane by means of ultraviolet absorption spectroscopy. The experimental results are compared with theory which is based on a finite-difference solution of boundary-layer equations. Finite-rate kinetics equations are included in the analysis. The analytic predictions are also compared with previously obtained experimental results which are based on probe measurements. Comparison is made between calculated and observed ignition distances.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71496 , E-7810 , Symp. on the Fluid Mech. of Combust.; May 13, 1974 - May 16, 1974; Montreal
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  • 85
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    Theoretical investigation of nonlinear three-dimensional instabilities in liquid rockets with real nozzles (1974)
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    Publication Date: 2019-06-27
    Description: An approximate analytical technique has been developed for the solution of nonlinear three-dimensional, transverse and axial combustion-instability problems that are frequently observed in liquid-propellant rocket motors. This theory is an extension and generalization of previous analyses, which could analyze either transverse or axial instabilities in liquid combustors with quasi-steady nozzles, to the practical situations of three-dimensional instabilities in combustors with conventional DeLaval nozzles. Unlike the quasi-steady nozzle, the presence of a conventional nozzle imposes restrictions upon the behavior of both the amplitudes and phases of the oscillations at the nozzle entrance plane. The applicability of the solution technique, which is based on the Galerkin method, is demonstrated by analyzing the nonlinear stability of a cylindrical liquid-rocket combustor with uniform injection of propellants at one end and a conventional nozzle at the other end. Crocco's pressure-sensitive time-lag model is used to describe the unsteady combustion process.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 86
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    Partial equilibrium model for predicting concentration of CO in combustion (1974)
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    Publication Date: 2019-06-27
    Description: A simple kinetic model, based upon the concept of partial equilibrium, is developed for predicting carbon monoxide concentrations in such steady-flow hydrocarbon-air combustion systems as gas-turbine combustors. The only two kinetic constraints used in the model are on the rate of change of the total number of gaseous particles in the system, and on the rate of change of the CO concentration. The accuracy of the model is verified by comparison with experimental results obtained by burning kerosene with air in a 130,000 Btu/hr atmospheric-pressure steady-flow burner. Burnt-gas cooling rates of 1,000,000 K/sec, about the magnitude encountered in the dilution zone of gas-turbine combustors, were obtained with a compact water-cooled heat exchanger. Good agreement between measured CO concentrations and the values predicted by the partial-equilibrium model was obtained.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 87
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    Fuel droplet combustion (1974)
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    Publication Date: 2019-06-27
    Description: An analytical model is developed that demonstrates the behavior of fuel drop ignition, and experimental results are presented that describe the effect of aerodynamic shattering on the process of fuel drop ignition. It is shown that the explosive ignition of a fuel drop which interacts with a shock wave in an oxidizing atmosphere depends upon the production of a fuel-oxidizer mixture in the wake of the original drop. The creation of this mixture is dependent on the formation of fine spray as a result of the aerodynamic shattering of the original fuel drop, the evaporation of the fine spray, and the mixing of the fuel vapor with the surrounding hot oxidizer. Only then does the explosive ignition occur as a result of the chemical reaction between the gaseous fuel and oxidizer.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Archiwum Procesow Spalania; 5; 2, 19; 1974
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  • 88
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    Peak pool boiling heat flux in viscous liquids (1974)
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    Publication Date: 2019-06-27
    Description: The stability of a gas jet in a surrounding viscous liquid is studied. An expression is developed for the critical velocity at which the jet becomes unstable in a returning viscous liquid. The stability analysis is made to correspond with the geometrical configuration of gas jets and liquid columns similar to those observed near the peak pool boiling heat flux. The critical velocity of the gas jet is then used to obtain the functional form of the peak heat flux on flat plates and cylindrical heaters. The expressions are compared with original observations of the peak heat flux in very viscous liquids on flat plate, and cylindrical, heaters at both earth-normal, and elevated, gravities.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 74-HT-J
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  • 89
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    Tricritical points in multicomponent fluid mixtures (1974)
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    Publication Date: 2019-06-27
    Description: In view of experimental considerations, we give a model-independent argument that the novel tricritical points in multicomponent fluid mixtures, where three phases simultaneously become critical, are points on the boundary of a single two-dimensional surface of critical points. This result is corroborated by the Landau model suggested by Griffiths. The relationship between these tricritical points and the complex 'higher-order' critical points proposed to exist in certain magnetic systems is elucidated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-785829 , AFOSR-74-1482TR , Physical Review A - General Physics; vol. 9
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  • 90
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    Hypervelocity impact heating of porous aluminum (1974)
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    Publication Date: 2019-06-27
    Description: Estimates of the thermal energy and other properties of the postshock condition are obtained for porous aluminum targets impacted by iron or aluminum projectiles, in the shock pressure range between about 0.4 and 8 Mbar. The starting point is the determination of a distinct Hugoniot equation for each value of porosity, from available experimental data. Rankine-Hugoniot equations and a Mie-Gruneisen equation of state supply the relations necessary for finding the thermodynamic properties of adiabatically relaxed materials. The results are of interest in such fields as ablation studies, meteoritics, and lunar topography.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Applied Physics; 45; June 197
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  • 91
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    Elementary solutions of coupled model equations in the kinetic theory of gases (1974)
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    Publication Date: 2019-06-27
    Description: The method of elementary solutions is employed to solve two coupled integrodifferential equations sufficient for determining temperature-density effects in a linearized BGK model in the kinetic theory of gases. Full-range completeness and orthogonality theorems are proved for the developed normal modes and the infinite-medium Green's function is constructed as an illustration of the full-range formalism. The appropriate homogeneous matrix Riemann problem is discussed, and half-range completeness and orthogonality theorems are proved for a certain subset of the normal modes. The required existence and uniqueness theorems relevant to the H matrix, basic to the half-range analysis, are proved, and an accurate and efficient computational method is discussed. The half-space temperature-slip problem is solved analytically, and a highly accurate value of the temperature-slip coefficient is reported.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Engineering Science; 12; June 197
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  • 92
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    Efficient stream distributions in radiative transfer theory (1974)
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    Publication Date: 2019-06-27
    Description: This paper discusses a new, computationally-efficient method for approximating the integro-differential equation of radiative transfer with a finite set of coupled differential equations for discrete streams. The method uses recommended spatial distributions of streams that are quite different from those typically used in that they are based on the symmetry of several regular Platonic solids. To facilitate the use of such distributions, an explicit, one-parameter relationship between the physical radiance and the abstract stream is formulated. The parameter is used to determine the minimum number of streams required in the radiative transfer model. Accuracy and computational efficiency are shown to be served best by choosing a stream distribution that is invariant to a large number of three space rotations. For various values of the above-mentioned parameter, the resulting recommended stream distribution is shown to be more computationally efficient than more conventional stream distributions. Finally, the incorporation of polarization in the stream definition is described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 14; July 197
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  • 93
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    Heat transfer and film cooling following injection through inclined circular tubes (1974)
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    Publication Date: 2019-06-27
    Description: Film cooling effectiveness and heat transfer are measured downstream of injection through discrete holes into a turbulent mainstream boundary layer. Air is injected through both a single hole and a row of holes spaced at three-diameter intervals and inclined at an angle of 35 deg to the main flow. There is little difference between the heat transfer coefficient with blowing and without blowing at low blowing rates (mass flux ratios). In fact, at low blowing rates, injection is found to decrease somewhat the heat transfer coefficient from that measured without blowing. As the mass flux ratio increases past unity, the heat transfer coefficient increases, especially with injection through a row of holes. The peak heat transfer is usually found at the edge of the spreading jets (i.e., between two holes). At a blowing rate near two, the lateral average of the heat transfer is as much as 27 percent higher than the heat transfer with no blowing. The increase in heat transfer is attributed to the interaction between the jets and the free stream, causing high levels of turbulence.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 74-HT-V
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  • 94
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    Electrohydrodynamic heat pipe experiments (1974)
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    Publication Date: 2019-06-27
    Description: Experiments with two electrohydrodynamic heat pipes are reported. Both devices employ an electromechanical flow structure for axial liquid flow and a capillary wicking structure for (1) collection of condensed liquid at the cooled end and (2) distribution of this liquid at the heated end. One device has circumferential grooving for the capillary structure and the other has feltmetal wicking. The experiments successfully demonstrate the electrohydrodynamic heat pipe concept. Compatibility of the two circumferential wick structures with an axial electromechanical flow structure is also demonstrated. A significant mismatch of the capillary groove and electrohydrodynamic pumping capabilities results in severe hydrodynamic burn-out limiting in the first heat pipe. Both devices have very poor over-all thermal conductances of the order of 1-2 W/deg C, reflecting the generally poor heat-transfer properties of the dielectric working fluids required in electrohydrodynamic heat pipes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Applied Physics; 45; May 1974
    Format: text
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  • 95
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    Growth of turbulent boundary layers over nonstationary boundaries (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel data are presented which show that the velocity distribution in a turbulent boundary layer above a moving ground plane can be represented as a power law. The flows under consideration are encountered in studies of shock waves near solid boundaries and of the near-field drag of tube vehicles. The two wind tunnels used in the experiment were equipped with moving ground belts and employed porous suction plates to remove the normal tunnel boundary layer. The layers studied are, therefore, assumed to originate at the leading edge of the belt.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 12; Jan. 197
    Format: text
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  • 96
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    Liquid rocket combustion computer model with distributed energy release. DER computer program documentation and user's guide, volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program for analyzing rocket engine performance was developed. The program is concerned with the formation, distribution, flow, and combustion of liquid sprays and combustion product gases in conventional rocket combustion chambers. The capabilities of the program to determine the combustion characteristics of the rocket engine are described. Sample data code sheets show the correct sequence and formats for variable values and include notes concerning options to bypass the input of certain data. A seperate list defines the variables and indicates their required dimensions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-140026
    Format: application/pdf
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  • 97
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    Millimeter wave pumped parametric amplifier (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A negative resistance parametric amplifier is reported that employs a discrete varactor diode for high frequency pump excitation in the millimeter wave range.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Format: application/pdf
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  • 98
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    Thermal radiation analysis system (TRASYS) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Thermal Radiation Analysis System, TRASYS, is a digital computer software system with generalized capability to solve the radiation-related aspects of thermal analysis problems. When used in conjunction with a generalized thermal analyzer program any thermal problem that can be expressed in terms of a lumped parameter R-C thermal network can be solved. The function of TRASYS is twofold. It provides: (1) internode radiation interchange data; and (2) incident and absorbed heat rate data from environmental radiant heat sources. Data of both types is provided in a format directly usable by the thermal analyzer programs. One of the primary features of TRASYS is that it allows the user to write his own executive or driver program which organizes and directs the program library routines toward solution of each specific problem in the most expeditious manner. The user also may write his own output routines, thus the system data output can directly interface with any thermal analyzer using the R-C network concept.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134391 , MCR-74-100
    Format: application/pdf
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  • 99
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    Analysis of impingement heat transfer for two parallel liquid-metal slot jets (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical method is developed for determining heat transfer by impinging liquid-metal slot jets. The method involves mapping the jet flow region, which is bounded by free streamlines, into a potential plane where it becomes a uniform flow in a channel of constant width. The energy equation is transformed into potential plane coordinates and is solved in the channel flow region. Conformal mapping is then used to transform the solution back into the physical plane and obtain the desired heat-transfer characteristics. The analysis given here determines the heat-transfer characteristics for two parallel liquid-metal slot jets impinging normally against a uniformly heated flat plate. The liquid-metal assumptions are made that the jets are inviscid and that molecular conduction is dominating heat diffusion. Wall temperature distributions along the heated plate are obtained as a function of spacing between the jets and the jet Peclet number.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7772 , E-7906
    Format: application/pdf
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  • 100
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    Analytic and experimental evaluation of shadow shields and their support members for thermal control of space vehicles (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermal performance of shadow shields, and their support struts, for the thermal protection of cryogenic propellants in a simulated deep-space environment was investigated analytically and experimentally. Very low overall heat-transfer rates were obtained when highly reflective aluminized Mylar shadow shields were used. The thermal interactions between the shields and support struts were investigated with fair to good agreement between the analysis and experimental data. The exterior surface of both fiberglass and titanium struts was coated to reduce the heat input into the test tank. The vacuum level inside the test facility strongly influenced the heat-transfer rates.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7612 , E-7344
    Format: application/pdf
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