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  • PROPULSION SYSTEMS
  • THERMODYNAMICS AND COMBUSTION
  • 1970-1974  (301)
  • 1974  (301)
  • 1
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    Heat Transfer and Thermodynamics: a Compilation (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A compilation is presented for the dissemination of information on technological developments which have potential utility outside the aerospace and nuclear communities. Studies include theories and mechanical considerations in the transfer of heat and the thermodynamic properties of matter and the causes and effects of certain interactions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-5959(01)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal-Structural Evaluation of TD Ni-20Cr Thermal Protection System Panels (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The results of a thermal-structural test program to verify the performance of a metallic/radiative Thermal Protection System (TPS) under reentry conditions are presented. This TPS panel is suitable for multiple reentry, high L/D space vehicles, such as the NASA space shuttle, having surface temperatures up to 1200 C (2200 F). The TPS panel tested consists of a corrugation-stiffened, beaded-skin TD Ni-20Cr metallic heat shield backed by a flexible fibrous quartz and radiative shield insulative system. Test conditions simulated the critical heating and aerodynamic pressure environments expected during 100 repeated missions of a reentry vehicle. Temperatures were measured during each reentry cycle; heat-shield flatness surveys to measure permanent set of the metallic components were made every 10 cycles. The TPS panel, in spite of localized surface failures, performed its designated function.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132487
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Conformal mapping technique for two-dimensional porous media and jet impingement heat transfer (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Transpiration cooling and liquid metals both provide highly effective heat transfer. Using Darcy's law in porous media and the inviscid approximation for liquid metals, the local fluid velocity in these flows equals the gradient of a potential. The energy equation and flow region are simplified when transformed into potential plane coordinates. In these coordinates, the present problems are reduced to heat conduction solutions which are mapped into the physical geometry. Results are obtained for a porous region with simultaneously prescribed surface temperature and heat flux, heat transfer in a two-dimensional porous bed, and heat transfer for two liquid metal slot jets impinging on a heated plate.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Heat Transfer Conference; Sept. 3-7, 1974; Tokyo; Japan
    Format: text
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  • 4
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    Noncircular Orifice Holes and Advanced Fabrication Techniques for Liquid Rocket Injectors (Phases 1, 2, 3, and 4) (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: A comprehensive summary of the results of a cold-flow and hot-fire experimental study of the mixing and atomization characteristics of injector elements incorporating noncircular orifices is presented. Both liquid/liquid and gas/liquid element types are discussed. Unlike doublet and triplet elements (circular orifices only) were investigated for the liquid/liquid case while concentric tube elements were investigated for the gas/liquid case. It is concluded that noncircular shape can be employed to significant advantage in injector design for liquid rocket engines.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134315 , R-9271
    Format: application/pdf
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  • 5
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    An exact solution of a simplified two-phase plume model (1974)
    In:  Other Sources
    Details
    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
    Format: text
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  • 6
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    Optimal rocket thrust profile shaping using third degree spline function interpolation (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Optimal solid-rocket thrust profiles for the parallel-burn, solid-rocket-assisted space shuttle are investigated. Solid-rocket thrust profiles are simulated by using third-degree spline functions, with the values of the thrust ordinates defined as parameters. The profiles are optimized parametrically, using the Davidon-Fletcher-Powell penalty function method, by minimizing propellant weight subject to state and control inequality constraints and to terminal boundary conditions. This study shows that optimizing a control variable parametrically by using third-degree spline function interpolation allows the control to be shaped so that inequality constraints are strictly adhered to and all corners are eliminated. The absence of corners, which is realistic in nature, makes this method attractive from the viewpoint of solid rocket grain design.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 74-823 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
    Format: text
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  • 7
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    Cryogenic and low temperature heat pipe/cooler studies for spacecraft application (1974)
    In:  Other Sources
    Details
    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
    Format: text
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  • 8
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    An examination of injector/combustor design effects on scramjet performance (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Description of a simplified one-dimensional treatment of fuel injection for supersonic combustor performance analysis. Representative mixing efficiency variations for both parallel and cross-stream injection are obtained, and approximate means for estimating the length required for complete mixing are demonstrated. Comparisons of calculated and measured data show good agreement.
    Keywords: PROPULSION SYSTEMS
    Type: International Symposium on Air Breathing Engines; Mar 24, 1974 - Mar 29, 1974; Sheffield
    Format: text
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  • 9
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    Formulation of a distortion index based on peak compressor pressure ratios (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In order to effectively use a compressor face total-pressure distortion index as a measure of inlet-engine compatibility, a correlation of distortion amplitude with stall margin must be developed with minimal scatter. A recent analysis of data recorded in extensive distortion screen tests with the J85-GE-13 turbojet engine has resulted in a correlation based on compressor discharge pressure ratioed to the minimum pressure at the compressor face. Simply by determining compressor stall lines with a single hub radial distortion pattern, a single tip radial pattern, and with undistorted inflow, the overall compressor pressure ratio at stall for even the most complex distortion pattern was found to be predictable.
    Keywords: PROPULSION SYSTEMS
    Type: National Conference on Environmental Effects on Aircraft and Propulsion Systems; May 21, 1974 - May 23, 1974; Trenton, NJ
    Format: text
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  • 10
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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
    Details
    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
    Format: text
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