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  • Other Sources  (5)
  • FLUID MECHANICS AND HEAT TRANSFER  (2)
  • Tectonics  (2)
  • DEKORP 2, seismic processing/methodology, seismic attributes, reflection seismics  (1)
  • 1
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    Reflectivity variations of Variscan terranes in Germany (1991)
    Am. Geophys. Un.
    In:  Professional Paper, Continental Lithosphere: Deep Seismic Reflections, Washington, D.C., Am. Geophys. Un., vol. 22, no. 16, pp. 87-90, (ISBN 0080419208)
    Details
    Publication Date: 1991
    Keywords: Reflectivity ; Tectonics ; Deep seismic sounding (espec. cont. crust) ; Meissner ; Duerbaum ; Durbaum
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Oberpfalz Deep Seismic Reflection Survey and Velocity Studies (1989)
    Springer
    In:  Bull., Open-File Rept., The German Continental Deep Drilling Program (KTB), Site-Section Studies in the Oberpfalz and Schwarzwald, Berlin, Springer, vol. 65, no. 16, pp. 99-150, (ISBN 1-86239-165-3, vi + 330 pp.)
    Details
    Publication Date: 1989
    Keywords: KTB ; Deep seismic sounding (espec. cont. crust) ; Tectonics ; Reflection seismics ; Duerbaum ; Durbaum ; Ruehl ; Ruhl ; Meissner
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Energy- and power sections in seismic interpretation (1991)
    In:  In: Meissner et al. (eds), Continental Lithosphere: Deep seismic reflections, Geodynamics Series., 22, AGU, Washington, DC, pp. 409-415
    Details
    Publication Date: 1991
    Keywords: DEKORP 2, seismic processing/methodology, seismic attributes, reflection seismics
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    CITATION DEKORP
  • 4
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    Flow establishment in a generic scramjet combustor (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The establishment of a quasi-steady flow in a generic scramjet combustor was studied for the case of a time varying inflow to the combustor. Such transient flow is characteristic of the reflected shock tunnel and expansion tube test facilities. Several numerical simulations of hypervelocity flow through a straight duct combustor with either a side wall step fuel injector or a centrally located strut injector are presented. Comparisons were made between impulsively started but otherwise constant flow conditions (typical of the expansion tube or tailored operations of the reflected shock tunnel) and the relaxing flow produced by the 'undertailored' operations of the reflected shock tunnel. Generally the inviscid flow features, such as the shock pattern and pressure distribution, were unaffected by the time varying inlet conditions and approached steady state in approx. the times indicated by experimental correlations. However, viscous features, such as heat transfer and skin friction, were altered by the relaxing inlet flow conditions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-187467 , ICASE-90-77 , NAS 1.26:187467 , AD-A229670
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A comparative study of scramjet injection strategies for high Mach numbers flows (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A simple method for predicting the axial distribution of supersonic combustor thrust potential is described. A complementary technique for illustrating the spatial evolution and distribution of thrust potential and loss mechanisms in reacting flows is developed. Wall jet cases and swept ramp injector cases for Mach 17 and Mach 13.5 flight enthalpy inflow conditions are numerically modeled and analyzed using these techniques. The visualization of thrust potential in the combustor for the various cases examined provides a unique tool for increasing understanding of supersonic combustor performance potential.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 92-3287
    Format: text
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    NASA TECHNICAL REPORTS
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