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  • 1
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    Parametric Study of Solar Thermal Rocket Nozzle Performance (1996)
    American Society of Mechanical Engineers
    Details
    Publication Date: 1996-08-01
    Print ISSN: 0199-6231
    Electronic ISSN: 1528-8986
    Topics: Energy, Environment Protection, Nuclear Power Engineering
    Published by American Society of Mechanical Engineers
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    PAPER CURRENT
  • 2
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    ISWE: A Case Study of Technology Utilization (1998)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The International Space Welding Experiment is a joint project between the E.O. Paton Welding Institute of Kiev, Ukraine and the George C. Marshall Space Flight Center in Huntsville, Alabama. When an international partner is involved in a project, differences in design and testing philosophy can become a factor in the development of the hardware. This report addresses selected issues that arose during the ISWE hardware development as well as the solutions the ISWE team made.
    Keywords: Mechanical Engineering
    Type: NASA/TM-1998-206528 , M-845 , NAS 1.26:206528
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Mixing of Supersonic Streams (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Strutjet approach to Rocket Based Combined Cycle (RBCC) propulsion depends upon fuel-rich flows from the rocket nozzles and turbine exhaust products mixing with the ingested air for successful operation in the ramjet and scramjet modes. It is desirable to delay this mixing process in the air-augmented mode of operation present during low speed flight. A model of the Strutjet device has been built and is undergoing test to investigate the mixing of the streams as a function of distance from the Strutjet exit plane during simulated low speed flight conditions. Cold flow testing of a 1/6 scale Strutjet model is underway and nearing completion. Planar Laser Induced Fluorescence (PLIF) diagnostic methods are being employed to observe the mixing of the turbine exhaust gas with the gases from both the primary rockets and the ingested air simulating low speed, air augmented operation of the RBCC. The ratio of the pressure in the turbine exhaust duct to that in the rocket nozzle wall at the point of their intersection is the independent variable in these experiments. Tests were accomplished at values of 1.0, 1.5 and 2.0 for this parameter. Qualitative results illustrate the development of the mixing zone from the exit plane of the model to a distance of about 19 equivalent rocket nozzle exit diameters downstream. These data show the mixing to be confined in the vertical plane for all cases, The lateral expansion is more pronounced at a pressure ratio of 1.0 and suggests that mixing with the ingested flow would be likely beginning at a distance of 7 nozzle exit diameters downstream of the nozzle exit plane.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: JANNAF Airbreathing Propulsion Subcommittee and 35th Combustion Subcommittee Meeting; 1; 1-8; CPIA-Publ-682-Vol-1
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    High-Energy Space Propulsion Based on Magnetized Target Fusion (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Magnetized target fusion is an approach in which a magnetized target plasma is compressed inertially by an imploding material wall. A high energy plasma liner may be used to produce the required implosion. The plasma liner is formed by the merging of a number of high momentum plasma jets converging towards the center of a sphere where two compact toroids have been introduced. Preliminary 3-D hydrodynamics modeling results using the SPHINX code of Los Alamos National Laboratory have been very encouraging and confirm earlier theoretical expectations. The concept appears ready for experimental exploration and plans for doing so are being pursued. In this talk, we explore conceptually how this innovative fusion approach could be packaged for space propulsion for interplanetary travel. We discuss the generally generic components of a baseline propulsion concept including the fusion engine, high velocity plasma accelerators, generators of compact toroids using conical theta pinches, magnetic nozzle, neutron absorption blanket, tritium reprocessing system, shock absorber, magnetohydrodynamic generator, capacitor pulsed power system, thermal management system, and micrometeorite shields.
    Keywords: Spacecraft Propulsion and Power
    Type: Jun 20, 1999 - Jun 23, 1999; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Mixing of Supersonic Streams (1998)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Strutjet approach to Rocket Based Combined Cycle (RBCC) propulsion depends upon fuel-rich flows from the rocket nozzles and turbine exhaust products mixing with the ingested air for successful operation in the ramjet and scramjet modes. It is desirable to delay this mixing process in the air-augmented mode of operation present during low speed flight. A model of the Strutjet device has been built and is undergoing test to investigate the mixing of the streams as a function of distance from the Strutjet exit plane during simulated low speed flight conditions. Cold flow testing of a 1/6 scale Strutjet model is underway and nearing completion. Planar Laser Induced Fluorescence (PLIF) diagnostic methods are being employed to observe the mixing of the turbine exhaust gas with the gases from both the primary rockets and the ingested air simulating low speed, air augmented operation of the RBCC. The ratio of the pressure in the turbine exhaust duct to that in the rocket nozzle wall at the point of their intersection is the independent variable in these experiments. Tests were accomplished at values of 1.0, 1.5 and 2.0 for this parameter. Qualitative results illustrate the development of the mixing zone from the exit plane of the model to a distance of about 10 rocket nozzle exit diameters downstream. These data show the mixing to be confined in the vertical plane for all cases, The lateral expansion is more pronounced at a pressure ratio of 1.0 and suggests that mixing with the ingested flow would be likely beginning at a distance of 7 nozzle exit diameters downstream of the nozzle exit plane.
    Keywords: Spacecraft Propulsion and Power
    Type: Dec 07, 1998 - Dec 11, 1998; Tucson, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Development of a new model for vibration-dissociation coupling in nitrogen (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A new model for vibration-dissociation coupling is derived using knowledge obtained from a simulation of the vibrational relaxation of heated nitrogen by collisional processes. This bilevel model is based on the assumption that nitrogen can be represented by two molecular species. The vibrational energy relaxation is represented by a modified form of the Landau-Teller equation. The effects of the bilevel model on a typical hypervelocity flowfield computation are examined and compared to the Park TTv model. Specifically, it is found that the bilevel model exhibits a decreased dissociation rate. This is believed to be due to the inhibition of dissociation by nonequilibrium vibrational relaxation.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: AIAA PAPER 92-2853
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Uncertainty Analysis on Heat Transfer Correlations for RP-1 Fuel in Copper Tubing (2004)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: NASA is studying kerosene (RP-1) for application in Next Generation Launch Technology (NGLT). Accurate heat transfer correlations in narrow passages at high temperatures and pressures are needed. Hydrocarbon fuels, such as RP-1, produce carbon deposition (coke) along the inside of tube walls when heated to high temperatures. A series of tests to measure the heat transfer using RP-1 fuel and examine the coking were performed in NASA Glenn Research Center's Heated Tube Facility. The facility models regenerative cooling by flowing room temperature RP-1 through resistively heated copper tubing. A Regression analysis is performed on the data to determine the heat transfer correlation for Nusselt number as a function of Reynolds and Prandtl numbers. Each measurement and calculation is analyzed to identify sources of uncertainty, including RP-1 property variations. Monte Carlo simulation is used to determine how each uncertainty source propagates through the regression and an overall uncertainty in predicted heat transfer coefficient. The implications of these uncertainties on engine design and ways to minimize existing uncertainties are discussed.
    Keywords: Propellants and Fuels
    Type: HAWK-TC-02 , 52nd JANNAF Joint Propulsion Meeting; May 10, 2004 - May 14, 2004; Las Vegas, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Heating requirements and nonadiabatic surface effects for a model in the NTF cryogenic wind tunnel (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A theoretical study has been made of the severity of nonadiabatic surface conditions arising from internal heat sources within a model in a cryogenic wind tunnel. Local surface heating is recognized as having an effect on the development of the boundary layer, which can introduce changes in the flow about the model and affect the wind tunnel data. The geometry was based on the NTF Pathfinder I wind tunnel model. A finite element heat transfer computer code was developed and used to compute the steady state temperature distribution within the body of the model, from which the surface temperature distribution was extracted. Particular three dimensional characteristics of the model were represented with various axisymmetric approximations of the geometry. This analysis identified regions on the surface of the model susceptible to surface heating and the magnitude of the respective surface temperatures. It was found that severe surface heating may occur in particular instances, but could be alleviated with adequate insulating material. The heat flux through the surface of the model was integrated to determine the net heat required to maintain the instrumentation cavity at the prescribed temperature. The influence of the nonadiabatic condition on boundary layer properties and on the validity of the wind tunnel simulation was also investigated.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 88-2044 , Aerodynamic Testing Conference; May 18, 1988 - May 20, 1988; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A theoretical study of non-adiabatic surface effects for a model in the NTF cryogenic wind tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A theoretical analysis was made of the severity and effect of nonadiabatic surface conditions for a model in the NTF cryogenic wind tunnel. The nonadiabatic condition arises from heaters that are used to maintain a constant thermal environment for instrumentation internal to the model. The analysis was made for several axi-symmetric representations of a fuselage cavity, using a finite element heat conduction code. Potential flow and boundary layer codes were used to calculate the convection condition for the exterior surface of the model. The results of the steady state analysis show that it is possible to maintain the surface temperature very near the adiabatic value, with the judicious use of insulating material. Even for the most severe nonadiabatic condition studied, the effects on skin friction drag and displacement thickness were only marginally significant. The thermal analysis also provided an estimate of the power required to maintain a specified cavity temperature.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3924 , NAS 1.26:3924 , TR-83-4975-02
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Numerical simulation of film-cooled ablative rocket nozzles (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective of this research effort was to evaluate the impact of incorporating an additional cooling port downstream between the injector and nozzle throat in the NASA Fast Track chamber. A numerical model of the chamber was developed for the analysis. The analysis did not model ablation but instead correlated the initial ablation rate with the initial nozzle wall temperature distribution. The results of this study provide guidance in the development of a potentially lighter, second generation ablative rocket nozzle which maintains desired performance levels.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-CR-201490 , NAS 1.26:201490 , TR-96-002
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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