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  • 1
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    Analysis of a hydrocarbon scramjet with augmented preburning (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of a feasibility study of a hydrocarbon scramjet design utilizing an augmented preburner upstream of the main fuel injector locations. The combustor design evaluated here is for a small hypersonic research vehicle. It consists of a preburner into which a small amount of fuel is burned with on-board liquid oxygen and injected into the main airflow, upstream of the main fuel injector locations, thus ensuring that combustion is present and uninterrupted. Two degrees of analysis are presented including a one-dimensional cycle analysis and a complete computational fluid dynamic analysis with finite-rate chemistry and a two-equation turbulence model. Comparison of these analyses show good agreement when the CFD-predicted fuel consumption schedule is used in the cycle analysis.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3425
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development of an upwind, finite-volume code with finite-rate chemistry (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Under this grant, two numerical algorithms were developed to predict the flow of viscous, hypersonic, chemically reacting gases over three-dimensional bodies. Both algorithms take advantage of the benefits of upwind differencing, total variation diminishing techniques, and a finite-volume framework, but obtain their solution in two separate manners. The first algorithm is a zonal, time-marching scheme, and is generally used to obtain solutions in the subsonic portions of the flow field. The second algorithm is a much less expensive, space-marching scheme and can be used for the computation of the larger, supersonic portion of the flow field. Both codes compute their interface fluxes with a temporal Riemann solver and the resulting schemes are made fully implicit including the chemical source terms and boundary conditions. Strong coupling is used between the fluid dynamic, chemical, and turbulence equations. These codes have been validated on numerous hypersonic test cases and have provided excellent comparison with existing data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-196749 , NAS 1.26:196749 , MCAT-94-01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A set of strongly coupled, upwind algorithms for computing flows in chemical nonequilibrium (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Two new algorithms have been developed to predict the flow of viscous, hypersonic, chemically reacting gases over three-dimensional bodies. Both take advantage of the benefits of upwind differencing, Total Variation Diminishing (TVD) techniques and of a finite-volume framework, but obtain their solution in two separate manners. The first algorithym is a time-marching scheme, and is generally used to obtain solutions in the subsonic portions of the flow field. The second algorithm is a much less expensive, space-marching scheme and can be used for the computation of the larger, supersonic portion of the flow field. Both codes compute their interface fluxes with a new temporal Riemann solver and the resulting schemes are made fully implicit including the chemical source terms.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0199
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A new computational model for the prediction of mass loading phenomena for solar wind interactions with cometary and planetary ionospheres (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The modified gasdynamic convected-magnetic-field MHD model developed by Spreiter and Stahara (1980) to simulate the supersonic flow of the solar wind past planetary magnetoionospheres is extended to account for cases (such as Venus and comets) in which significant numbers of neutral atmospheric atoms become ionized in the surrounding flow and add to its momentum, energy, and mass. The mathematical model and the solution procedures for the nose and tail regions are explained; typical computational grids are shown; and numerical results for a comet and for the Venus ionosheath and bow shock are presented graphically. It is found that the bow shock weakens and moves further upstream of the obstacle as mass loading is increased and the flow upstream of the bow shock becomes more compressed.
    Keywords: SOLAR PHYSICS
    Type: AIAA PAPER 87-1410
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Computation of viscous blast wave solutions with an upwind finite volume method (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A fully conservative, viscous, implicit, upwind, finite-volume scheme for the thin-layer Navier-Stokes equations is described with application to blast wave flow fields. In this scheme, shocks are captured without the oscillations typical of central differencing techniques and wave speeds are accurately predicted. The finite volume philosophy ensures conservation and since boundary conditions are also treated conservatively, accurate reflections of waves from surfaces are assured. Viscous terms in the governing equations are treated in a manner consistent with the finite volume philosophy, resulting in very accurate prediction of boundary layer quantities. Numerical results are presented for four viscous problems: a steady boundary layer, a shock-induced boundary layer, a blast wave/cylinder interaction and a blast wave/supersonic missile interaction. Comparisons of the results with an established boundary layer code, similarity solution, and experimental data show excellent agreement.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 87-1290
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Development of an upwind, finite-volume code with finite-rate chemistry (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Under this grant, two numerical algorithms were developed to predict the flow of viscous, hypersonic, chemically reacting gases over three-dimensional bodies. Both algorithms take advantage of the benefits of upwind differencing, total variation diminishing techniques and of a finite-volume framework, but obtain their solution in two separate manners. The first algorithm is a zonal, time-marching scheme, and is generally used to obtain solutions in the subsonic portions of the flow field. The second algorithm is a much less expensive, space-marching scheme and can be used for the computation of the larger, supersonic portion of the flow field. Both codes compute their interface fluxes with a temporal Riemann solver and the resulting schemes are made fully implicit including the chemical source terms and boundary conditions. Strong coupling is used between the fluid dynamic, chemical and turbulence equations. These codes have been validated on numerous hypersonic test cases and have provided excellent comparison with existing data. This report summarizes the research that took place from August 1,1994 to January 1, 1995.
    Keywords: AERODYNAMICS
    Type: NASA-CR-197747 , NAS 1.26:197747 , MCAT-95-01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Analysis of a hypersonic waverider research vehicle with a hydrocarbon scramjet engine (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of a feasibility study of a hypersonic waverider research vehicle with a hydrocarbon scramjet engine are presented. The integrated waverider/scramjet geometry is first optimized with a vehicle synthesis code to produce a maximum product of the lift-to-drag ratio and the cycle specific impulse, hence cruise range. Computational fluid dynamics (CFD) is then employed to provide a nose-to-tail analysis of the system at the on-design conditions. Some differences are noted between the results of the two analysis techniques. A comparison of experimental, engineering analysis and CFD results on a waverider forebody are also included for validation.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 93-0509 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 14 p.
    Format: text
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    NASA TECHNICAL REPORTS
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