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  • Other Sources  (920)
  • AERODYNAMICS  (383)
  • AIRCRAFT PROPULSION AND POWER  (270)
  • FLUID MECHANICS AND HEAT TRANSFER  (220)
  • 42.75
  • Biochemistry and Biotechnology
  • Seismology
  • 1975-1979  (920)
  • 1977  (920)
  • 1
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    Earthquake stress drops, ambient tectonic stresses and stresses that drive plate motions (1977)
    In:  Pageoph, Luxembourg, Conseil de l'Europe, vol. 115, no. 7055, pp. 441-458, pp. B05S07, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Stress drop ; Tectonics ; Stress ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Lithospheric slab penetration into the lower mantle beneath the Sea of Okhotsk (1977)
    In:  Z. Geophys., Reykjavík, Icelandic Meteorological Office, Ministry for the Environment University of Iceland, vol. 43, no. 5, pp. 473-496, pp. TC1011, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1977
    Keywords: Subduction zone ; Seismology ; USSR ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    On the telemetered array system for microearthquake observation at Abuyama Seismological Observatory (1977)
    In:  J. Seism. Soc. Japan, Basel, Elsevier Science Publishers, vol. 30, no. 1-2, pp. 91-106, pp. B03304, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Seismic arrays ; Detectors ; sta
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Study of the attenuation and azimuthal dependence of seismic wave propagation in the southeastern United States (1977)
    In:  Bull. Seism. Soc. Am., Berlin, Schweizerbart'sche Verlagsbuchhandlung, vol. 67, no. 7, pp. 1503-1513, pp. L14306, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Waves ; Attenuation ; Anisotropy ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    A fast epicenter location program (1977)
    In:  Bull. Seism. Soc. Am., Kunming, China, 4, vol. 67, no. 2, pp. 425-431, pp. L10314, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Location ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Importance of physical dispersion in surface wave and free oscillation problems: Review (1977)
    In:  Rev. Geophys. Space Phys., Tokyo, Tokyo University, vol. 15, no. 9, pp. 105-112, pp. 2265, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1977
    Keywords: Review article ; Surface waves ; Dispersion ; (The Earth's free) oscillations ; Seismology ; RGSP
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Energy release in great earthquakes (1977)
    In:  J. Geophys. Res., Tokyo, Tokyo University, vol. 82, no. 9, pp. 2981-2987, pp. 2265, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Source ; Source parameters ; Magnitude ; seismic Moment ; Energy (of earthquakes) ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Earth flattening approximation for body waves derived from geometric ray theory - improvements, corrections and range of applicability (1977)
    In:  J. Geophys., Warszawa, American Geophysical Union, vol. 42, no. 1+2, pp. 429-436, pp. L08304, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Theoret. geophys. ; Earth model, also for more shallow analyses ! ; Seismology ; Muller
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    The structure of the outer core from SKS amplitudes and travel times (1977)
    In:  Bull. Seism. Soc. Am., Würzburg, Physica-Verlag, vol. 67, no. 1, pp. 1541-1554, pp. L24313, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Travel time ; Amplitude ; earth Core ; Mueller ; Muller ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    High-frequency radiation from crack (stress drop) models of earthquake faulting (1977)
    In:  Geophys. J. R. astr. Soc., San Francisco, Pergamon, vol. 51, no. 3-4, pp. 625-651, pp. B05315, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Radiation pattern ; High frequency ... ; Source ; Seismology ; cracks and fractures (.NE. fracturing) ; Modelling ; GJRaS ; nokms
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Source mechanism of volcanic tremor: Fluid-driven crack models and their application to the 1963 Kilauea eruption (1977)
    In:  J. Volcanol. Geotherm. Res., Tokyo, Inst. f. Theoret. Geodäsie, vol. 2, no. 3, pp. 259-287
    Details
    Publication Date: 1977
    Keywords: Source ; Seismology ; Volcanology ; Fluids ; cracks and fractures (.NE. fracturing) ; Hawaii ; Modelling ; Rock mechanics ; JVGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Seismic sources with observable glut moments of spatial degree two (1977)
    In:  Geophys. J. R. astr. Soc., Washington D.C., Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 51, no. 6, pp. 27-45, pp. L08305
    Details
    Publication Date: 1977
    Keywords: Moment tensor ; Fault plane solution, focal mechanism ; Seismology ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    A numerical study of two-dimensional spontaneous rupture propagation (1977)
    In:  Geophys. J. R. astr. Soc., Warszawa, Army Corps of Engineers, Woodward-Clyde Consultants, vol. 50, no. 3, pp. 643-668, pp. 1013, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1977
    Keywords: Two-dimensional ; Fracture ; Modelling ; Source ; Seismology ; GJRaS ; nokms
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    The relationship between anelastic attenuation and regional amplitude anomalies of shortperiod P-waves in North America (1977)
    In:  Bull. Seism. Soc. Am., London, 416 pp., Geological Society, vol. 67, no. 5621, pp. 1303-1317, pp. L18607, (ISBN 1-86239-117-3)
    Details
    Publication Date: 1977
    Keywords: Seismology ; P-waves ; Attenuation ; Inelastic ; Absorption ; High frequency ... ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Large-scale heterogeneities in the lower mantle (1977)
    In:  J. Geophys. Res., Luxembourg, U.S. Geological Survey, vol. 82, no. 3-4, pp. 239-255, pp. B05309, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1977
    Keywords: Inhomogeneity ; Seismology ; JGR ; Dziewonski
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Matrix and Stokes vector representations of detectors for polarized waveforms: Theory, with some applications to teleseismic waves (1977)
    In:  Geophys. J. R. astr. Soc., Basel, Inst. f. Geophys., Ruhr-Univ. Bochum, vol. 51, no. 3, pp. 583-603, pp. 1009, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Description: zit. bei Park et al. (1987)
    Keywords: Seismology ; Polarization ; Detectors ; Data analysis / ~ processing ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    Eine seismotektonische Bearbeitung des Erdbebens von Messina im Jahre 1908 (1977)
    Bundesanstalt für Geowissenschaften und Rohstoffe
    In:  Geologisches Jahrbuch, Hannover, Bundesanstalt für Geowissenschaften und Rohstoffe, vol. E11, no. 1, pp. 267-286, pp. 1175, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Tectonics ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 18
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    Seismische Oberflächenwellen (1977)
    In:  J. Geophys., Luxembourg, Conseil de l'Europe, vol. 42, no. 1, pp. 283-328, pp. B09316, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; PIC ; gab ; Surface waves ; Review article ; Mueller ; Muller
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    BIBLIOGRAPHY SEISMOLOGY
  • 19
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    Real-time detection and location of local seismic events in Central California (1977)
    In:  Bull. Seism. Soc. Am., Berlin, Pergamon, vol. 67, no. 5, pp. 433-452, pp. B04306, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Detectors ; Location ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 20
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    Monitoring Underground Nuclear Explosions (1977)
    Elsevier
    In:  Amsterdam, 440 pp., Elsevier, vol. 231, no. 3, pp. 2-203, (ISBN 0-470-02298-1)
    Details
    Publication Date: 1977
    Keywords: Textbook of geophysics ; Nuclear explosion ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 21
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    Seismic source location in the Ruhr district (1977)
    Trans Tech Publ.
    In:  Professional Paper, Proc. 1. Conf. acoustic emission/microseism. activity in geol. struc. and materials, Clausthal, Trans Tech Publ., vol. 51, no. 16, pp. 235-242, (ISBN 1-86239-165-3, vi + 330 pp.)
    Details
    Publication Date: 1977
    Keywords: BUG ; Location ; Seismology ; Acoustic emission
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  • 22
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    Determination of the three-dimensional seismic structure of the lithosphere (1977)
    In:  J. Geophys. Res., Tokyo, Inst. f. Theoret. Geodäsie, vol. 82, no. 3, pp. 277-296
    Details
    Publication Date: 1977
    Keywords: Seismology ; Inversion ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 23
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    Quantitative prediction of strong motion for a potential earthquake fault (1977)
    In:  Annali di Geofisica, Tokyo, Inst. f. Theoret. Geodäsie, vol. XXX, no. 1-2, pp. 341-368
    Details
    Publication Date: 1977
    Keywords: Modelling ; Strong motions ; Fault zone ; Seismology ; nokms
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    BIBLIOGRAPHY SEISMOLOGY
  • 24
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    Interpreting the seismic glut moments of total degree two or less (1977)
    In:  Geophys. J. R. astr. Soc., Washington D.C., Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 51, no. 6, pp. 1-25, pp. L08305
    Details
    Publication Date: 1977
    Keywords: Moment tensor ; Fault plane solution, focal mechanism ; Seismology ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 25
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    Theoretical seismograms of core phases calculated by frequency-dependent full wave theory and their interpretation (1977)
    In:  Geophys. J. R. astr. Soc., Taipei, Elsevier, vol. 51, no. 1, pp. 275-312, pp. TC1002, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Waves ; caustics ; Synthetic seismograms ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 26
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    An interactive epicenter location procedure for the Resmac seismic array: I (1977)
    In:  Bull. Seism. Soc. Am., Berlin, Inst. Electrical & Electronics Engineers, vol. 67, no. 6, pp. 1577-1586, pp. B04307, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1977
    Keywords: Location ; Seismic arrays ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 27
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    Magnitude of great shallow earthquakes from 1904 to 1952 (1977)
    In:  Bull. Seism. Soc. Am., Regensburg, Inst. Electrical & Electronics Engineers, vol. 67, no. 3, pp. 587-598, pp. TC5001, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1977
    Keywords: Magnitude ; Earthquake catalog ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 28
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    Local magnitudes, seismic moments, and coda durations for earthquakes near Oroville, California (1977)
    In:  Bull. Seism. Soc. Am., Washington D.C., Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 67, no. 2, pp. 615-629, pp. L09611
    Details
    Publication Date: 1977
    Keywords: seismic Moment ; Seismology ; Magnitude ; Moment tensor ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 29
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    The monochromatic earthquake magnitude (1977)
    In:  Publ. Inst. Geoph. Pol. Acad. Sc., Hoboken, NJ, 633 pp. + CD-ROM, Pergamon, vol. A-5(166), no. 19, pp. 145-154, pp. B05309, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1977
    Keywords: Frequency ; Seismology ; Spectrum ; Magnitude
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    BIBLIOGRAPHY SEISMOLOGY
  • 30
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    Kinetic shear resistance, fluid pressures and radiation efficiency during seismic faulting (1977)
    In:  Pageoph, Dordrecht, D. Reidel, vol. 115, no. 5, pp. 387-400, pp. TC5003, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Friction ; Fluids ; Seismology ; Fracture
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    BIBLIOGRAPHY SEISMOLOGY
  • 31
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    A study of northeastern North American spectral moments, magnitudes, and intensities (1977)
    In:  Bull. Seism. Soc. Am., Leyden, Noordhoff International Publishing, vol. 67, no. 3, pp. 599-614, pp. B04306, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; seismic Moment ; Spectrum ; Magnitude ; Intensity ; Source parameters ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 32
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    Macroseismic study and the implications of structural damage of two recent major earthquakes in the Jordan rift (1977)
    In:  Bull. Seismo. Soc. Amer., Veldhoven, Kluwer, vol. 67, no. 1-2, pp. 1607-1613, pp. B05302, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Intensity ; Seismology ; Fault zone ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 33
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    Seismotektonische Karte der Schweiz, 1:500000, Erläuterungen (1977)
    Inst. für Geophys., ETH Zürich
    In:  Berlin, 254 pp., Inst. für Geophys., ETH Zürich, vol. 15, no. Publ. No. 12, pp. 585, (ISBN 1-85233-708-7)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Seismicity ; Tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 34
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    A three-component single-station maximum-likelihood surface wave processor (1977)
    Teledyne Geotech
    In:  Seismic Data Analysis Center report, Alexandria, Virginia, Teledyne Geotech, vol. 10, no. TR-77-14, pp. 484-486, (ISBN 3-933346-037)
    Details
    Publication Date: 1977
    Description: LS-Fit eines Polarisations-Modells im Frequenzbereich, Anwendung zur Abschätzung von Parametern wie Azimut für P-Wellen im kurzperiodischen Band und Rayleigh-Wellen im langperiodischen Band.
    Keywords: Seismology ; Maximum likelihood ; Polarization
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  • 35
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    The upper mantle under western Europe inferred from the dispersion of Rayleigh modes (1977)
    In:  J. Geophys., Tokyo, Dt. Geophys. Ges., vol. 43, no. 1-4, pp. 265-285, pp. 2389, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Surface waves ; Rayleigh waves ; Dispersion
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    BIBLIOGRAPHY SEISMOLOGY
  • 36
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    International Symposium on the Analysis of Seismicity and Seismic Hazard and Seismic Risk, 17. - 22. Oct. 1977/1978 (1977)
    Czechoslovak Academy of Sciences
    In:  Proceedings, Prag, Czechoslovak Academy of Sciences, vol. 10, no. WS-693 7-83, pp. 235-239, (ISBN 3-933346-037)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Seismicity ; Earthquake precursor: prediction research ; Earthquake risk ; Earthquake hazard ; Proceedings of a conference
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  • 37
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    Fault plane solutions using relative amplitudes of P and pP (1977)
    In:  Geophys. J. R. astr. Soc., Basle, Wiley, vol. 50, no. 5441, pp. 381-394, pp. 1264, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Source ; Seismology ; Fault plane solution, focal mechanism ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 38
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    Apparent stress and stress drop for intraplate earthquakes and tectonic stress in the plates (1977)
    In:  Pageoph, Luxembourg, National Academy of Sciences of the USA, vol. 115, no. 6, pp. 317-332, pp. B05311, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Stress ; Stress drop ; Tectonics
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  • 39
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    Spectral changes of fore- and aftershocks of the Haicheng earthquake (1977)
    In:  Acta Geophysica Sinica, Kunming, China, 3-4, vol. 20, no. 1-2, pp. 125-130, pp. B05301, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Fore-shocks ; Aftershocks ; Earthquake ; China
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  • 40
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    Physics of the Earth (1977)
    Wiley
    In:  New York, Wiley, vol. 25, no. Publ. No. 12, pp. 95-104, (ISBN: 0-08-043930-6)
    Details
    Publication Date: 1977
    Keywords: Textbook of geophysics ; Seismology ; Gravimetry, Gravitation ; TIDES ; Geomagnetics ; Geothermics
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  • 41
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    Geometry of Benioff zones: Lateral segmentation and downwards bending of the subducted lithosphere (1977)
    AGU
    In:  Bull., Polar Proj. OP-O3A4, Island Arcs, Deep Sea Trenches and Back Arc Basins, Englewood Cliffs, AGU, vol. 1, no. XVI:, pp. 99-114, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1977
    Keywords: Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Seismicity ; Subduction zone ; Seismology ; Inhomogeneity
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  • 42
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    Earthquake detectability estimates for 478 globally distributed seismograph stations (1977)
    In:  Phys. Earth Plan. Int., Luxembourg, National Academy of Sciences of the USA, vol. 15, no. 1, pp. P24-P32, pp. B05311, (ISSN: 1340-4202)
    Details
    Publication Date: 1977
    Keywords: Nuclear explosion ; Seismology ; Detectors ; Seismic networks ; PEPI
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    BIBLIOGRAPHY SEISMOLOGY
  • 43
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    Ray Methods in Seismology (1977)
    Charles Univ. Press
    In:  Prague, 214 pp., Charles Univ. Press, vol. 42, no. 3, pp. 275-291, (0-596-00648-9, 3rd edition 2005. XXII, 509 pp.)
    Details
    Publication Date: 1977
    Keywords: Seismology ; Textbook of geophysics ; Seismics (controlled source seismology) ; Ray seismics ; Ray tracing ; Cerveny ; Psencik ; Synthetic seismograms
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  • 44
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    Direct inversion of transmission synthetic seismograms (1977)
    In:  Preprint, Madrid, European Association of Exploration Geophysicists, vol. C 560, 183 pp., no. 8, pp. 129-132, (ISBN 3-933346-037)
    Details
    Publication Date: 1977
    Keywords: Inversion ; Synthetic seismograms ; Seismology ; Seismics (controlled source seismology)
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  • 45
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    Die Anelastizität im europäischen Raum (1977)
    Inst. f. Geophys., Univ.
    In:  Diplom-Arbeit, Hamburg, Inst. f. Geophys., Univ., vol. C 560, 183 pp., no. 6, pp. 1975-1982, (ISBN 3-933346-037)
    Details
    Publication Date: 1977
    Keywords: Inelastic ; Attenuation ; Seismology ; Seismics (controlled source seismology) ; Elasticity
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  • 46
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    A model for earthquake swarms (1977)
    In:  J. Geophys. Res., Zagreb, Conseil de l'Europe, vol. 82, no. 7, pp. 1347-1352, pp. 2118, (ISSN 0343-5164)
    Details
    Publication Date: 1977
    Keywords: Seismicity ; Source ; Seismology ; Modelling ; JGR
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  • 47
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    Phase-matched filters: application to the study of Rayleigh waves (1977)
    In:  Bull. Seism. Soc. Am., Zagreb, Conseil de l'Europe, vol. 67, no. 4, pp. 1259-1275, pp. L02307, (ISSN 0343-5164)
    Details
    Publication Date: 1977
    Keywords: Filter- ; Seismology ; Rayleigh waves ; BSSA
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  • 48
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    Transonic/supersonic inlet R and D past, present, and future (1977)
    In:  CASI
    Details
    Publication Date: 2004-10-07
    Keywords: AERODYNAMICS
    Type: NASA Lewis Research Center Inlet Workshop; p 427-480
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  • 49
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    Comments on wind-tunnel-flight correlations for the F-8 supercritical wing configurations (1977)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 111-120
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  • 50
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    Flow phenomena peculiar to calculation of compressible turbulent boundary layers (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Calculation procedures for compressible turbulent boundary layers were based upon techniques, modeling constants, etc., developed originally for the low speed case. Significant differences and new or altered physics which occur in the compressible case were considered, as compared with the low speed situation. Possible pitfalls and sources of inaccuracy in the calculations were indicated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Calculation Methods for Compressible Turbulent Boundary Layers, 1976; p 9-46
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  • 51
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    Aircraft (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The physical principles of flight, and the consideration of atmospheric composition and aerodynamic forces in the design and construction of various types of aircraft are discussed. Flight characteristics are described for helicopters, rotary-wing aircraft, short and vertical takeoff aircraft, and tailess or variable geometry wing aircraft. Flow characteristics at various speeds are also discussed.
    Keywords: AERODYNAMICS
    Type: Soviet Aircraft and Rockets (NASA-TT-F-770); p 24-80
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  • 52
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    Aircraft engines (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Thrust and weight requirements of aircraft engines in general are discussed. The characteristics and operating principles of various types of air breathing and rocket engines are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Soviet Aircraft and Rockets (NASA-TT-F-770); p 81-139
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  • 53
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    Summary of calculation procedures for nonsimilar two- and three-dimensional compressible turbulent boundary layers (finite difference, finite element and weighted residual methods), appendix (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: This numerical prediction summary indicates the wide variety of such procedures which are available. Most procedures have detailed user manuals, and in many cases the codes are available. Many of the special effects treated by various methods (such as nonequilibrium or equilibrium chemistry, transition, roughness etc.) are indicated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Calculation Methods for Compressible Turbulent Boundary Layers, 1976; p 69-78
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  • 54
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    Calculation of three-dimensional compressible turbulent boundary layers (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: From comparisons of high speed data with low speed closure procedures using variable mean density, there does not appear to be any appreciable influence of compressibility upon turbulent shear stress modeling in compressible turbulent boundary layers, even for extreme cases such as Mach 14 to 20 with a change in density across the layer of up to a factor of 100. Other evidence of apparent lack of compressibility caused new physics which may alter the shear stress for the compressible boundary layer cases including: (1) fluctuation Mach number was generally less than 1; (2) the shear stress distribution through the boundary layer was not a function of Mach number for zero pressure gradient flows; (3) the Morkovin hypothesis was valid up to Mach 5 (based on fluctuation data); (4) profile N power was not a function of Mach number, at least up to Mach 10; and (5) the nondimensional burst period was approximately the same as that for low speed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Calculation Methods for Compressible Turbulent Boundary Layers, 1976; p 47-68
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  • 55
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    Equations and closure methods (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Basic differential equations governing compressible turbulent boundary layer flow are reviewed, including conservation of mass and energy, momentum equations derived from Navier-Stokes equations, and equations of state. Closure procedures were broken down into: (1) simple or zeroth-order methods, (2) first-order or mean field closure methods, and (3) second-order or mean turbulence field methods.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Calculation Methods for Compressible Turbulent Boundary Layers, 1976; p 6-8
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  • 56
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    Three-dimensional low Reynolds number flows with a free surface (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The two-dimensional leveling problem (Degani, Gutfinger, 1976) is extended to three dimensions in the case where the flow Re number is very low and attention is paid to the free surface boundary condition with surface tension effects included. The no-slip boundary condition on the wall is observed. The numerical solution falls back on the Marker and Cell (MAC) method (Harlow and Welch, 1965) with the computation region divided into a finite number of stationary rectangular cells (or boxes in the 3-D case) and fluid flow traverses the cells (or boxes).
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Computational Physics; 24; May 1977
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  • 57
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    Numerical solution for subcritical flows by a transonic integral equation method (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The method presented makes use of a division of the region of integration into closed rectangular elements. The velocity is taken to be constant in each element. The integral equation is reduced to a matrix equation which can be solved by an appropriate iteration approach. The derivation and solution of the matrix equation are discussed and the matrix elements are considered. The described concepts were implemented for a nonlifting parabolic-arc airfoil.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Mar. 197
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  • 58
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    Derivation of an integral equation for transonic flows (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: It is noted that the nonlinear partial differential equation for the perturbation velocity potential and boundary conditions describing steady inviscid compressible transonic flow past a thin two-dimensional airfoil can be transformed into a singular integrodifferential equation and that differentiation of the latter yields an integral equation. Two forms of this integral equation currently exist: one for the singularity that is enclosed in an infinitely long strip of vanishing thickness and the other for the singularity that is enclosed in a vanishing circle. In the present article, a more general integral equation is derived by enclosing the singularity in a vanishing rectangular cavity of arbitrary aspect ratio. The two existing forms of this equation are deduced as special cases distinguished by the respective values for the aspect ratio (infinity for the first form and unity for the second).
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Feb. 197
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  • 59
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    Flow characteristics in an expansion tunnel as inferred from velocity measurements (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A photoionization technique was used to study flow characteristics in an expansion tunnel. Vertical surveys of the axial component of flow velocity just downstream from the nozzle exit were obtained, and estimates of freestream density were inferred from the velocity measurement technique. The pitot pressure was measured and compared to the average axial component of velocity as a function of time for the two cases when air and CO2 were used as test gases. Vertical velocity and static density profiles at the nozzle exit are presented for the case when CO2 was used as test gas. Experimental results were used to determine the diameter and uniformity of the test core at the nozzle exit and the duration of the quasi-steady flow period. These data are relevant to evaluation of the suitability of operating an expansion tube as an expansion tunnel. The expansion tunnel is an expansion tube with a conical nozzle positioned at the exit of the acceleration section, so that nozzle entrance flow conditions are hypersonic and characterized by hypervelocity.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Sept
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  • 60
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    Streamtube analysis of a hydrogen-burning scramjet exhaust and simulation technique (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A scramjet/airframe integration program and a technique for simulating thermally perfect scramjet exhaust flows (freon/argon gas blends) is studied to extend the technique to more complicated flows approaching the actual exhaust flow in complexity. The state of the flow and the accuracy of the substitute gas simulation are analyzed in the case of a shock discontinuity present. Findings are: scramjet exhaust flow is essentially frozen throughout the expansion at Mach 6 and Mach 8; flow behind moderate shocks remains frozen; the technique can accurately track static distributions in scramjet exhaust flows (shocked or unshocked).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Aircraft; 14; Sept
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  • 61
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    Kinetic theory analysis of rarefied gas flow through finite length slots (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A kinetic-theory analysis is made of the flow of a rarefied monatomic gas through a two-dimensional slot connecting two reservoirs. Numerical solutions are obtained by the moment and discrete-ordinate methods. The former method portrays the transition-regime characteristics well but has limitations in the free-molecule regime. The latter method gives accurate results in the free-molecule and slip regimes and bolsters confidence in the accuracy of the transition-regime results. The numerical solution for the mass flux through the slot agrees well with an approximate analytical solution of the moment equations for length-to-width ratios from 6 to 0.5, pressure ratios from 0.8 to 0.1, and Knudsen numbers from 5 to 0.5.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 20; June 197
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  • 62
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    Low Reynolds number flow past a blunt axisymmetric body at angle of attack (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Low Reynolds number flow of an ideal gas over a blunt axisymmetric body of large half-angle at small angles of attack is investigated, for the case of laminar hypersonic flow. Time-varying viscous shock layer equations describing the flowfield are obtained from the full Navier-Stokes system by keeping terms to second order in the inverse square root of Re in both viscous and inviscid regions; the equations are valid for moderate to high Re. Drag, skin friction, and heating rates were obtained at small (or zero) angles of attack. Conditions experienced by planetary entry probes during the high-altitude (early) legs of an atmospheric entry trajectory are pertinent to the problem.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Aug. 197
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  • 63
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    Evaluation of flight spoilers for vortex alleviation (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes the facilities and test procedures used in a series of wind-tunnel and full-scale flight investigations of the effectiveness of flight spoilers currently existing on wide-bodied transport jet aircraft when used as trailing vortex hazard alleviation devices. Examples of the results of such studies include the variation of trailing wing rolling-moment coefficient with downstream distance behind a B-747 airplane model with various segments of its flight spoilers deflected 45 deg, and comparisons with models without spoilers deflected. It is concluded that the existing flight spoilers on the B-747 are effective as trailing vortex attenuators.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; Aug. 197
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  • 64
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    The effect of ablation injection on radiative and convective heating (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A viscous shock-layer analysis for calculating high energy equilibrium flow fields about blunt axisymmetric bodies is applied to the problem of massive ablation injection with radiation transport. A nongray radiation model is used that accounts for both line and continuum radiation. The solution method is direct and provides both stagnation and downstream solutions. Results for shock heated air show that phenolic-nylon injection is substantially more effective in reducing the wall radiant flux than air injection. Also, for large included body angles, the wall radiative flux and the coupled phenolic-nylon injection rate do not continue to decrease with increasing distance downstream.
    Keywords: AERODYNAMICS
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  • 65
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    Comment on 'Drag coefficient of spheres in continuum and rarefied flows' (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A paper by Henderson (1976) provides a method of predicting experimental sphere drag data. This approach uses two equations for the drag coefficient, one for relative Mach number less than one, one for relative Mach number greater than 1.75. For relative Mach numbers between these limits a linear interpolation procedure is followed. In a comment on this paper, it is claimed, on the basis of comparing predictions with experimental results, that a method proposed by Walsh (1975) gives better predictions of the drag coefficient for relative Mach numbers less than 1.75, provided that a modification of the procedure is made for relative Mach numbers less than 0.1. For values over 1.75, both methods are considered equally accurate. In a reply to this comment, it is agreed that the Walsh method is more accurate when Reynolds numbers are within a range between 20 and 200, and Mach numbers are between 0.5 and 1.25. Presumed errors and possible limitations in the Walsh procedure for predicting drag coefficients are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; June 197
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  • 66
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    Vortex lattice prediction of subsonic aerodynamics of hypersonic vehicle concepts (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The vortex lattice method introduced by Lamar and Gloss (1975) was applied to the prediction of subsonic aerodynamic characteristics of hypersonic body-wing configurations. The reliability of the method was assessed through comparison of the calculated and observed aerodynamic performances of two National Hypersonic Flight Research Facility craft at Mach 0.2. The investigation indicated that a vortex lattice model involving 120 or more panel elements can give good results for the lift and induced drag coefficients of the craft, as well as for the pitching moment at angles of attack below 10 to 15 deg. Automated processes for calculating the local slopes of mean-camber surfaces may also render the method suitable for use in preliminary design phases.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; Oct. 197
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  • 67
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    Cooling effectiveness of slot injection into a turbulent boundary layer (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The cooling effectiveness of injection through multiple flush slots at an angle of 10 deg was studied experimentally in a wind tunnel. Air was injected from one to four slots into a turbulent Mach 6 boundary layer. The slot mass flow ratio is defined, and data which describe the dependence of the cooling effectiveness on the slot mass flow ratio are presented. Experimental values are indicated graphically for various cases of single and multiple slot injection, where the total mass injection (i.e., the sum of flow rates from each slot) is the same for each case. The results show that, for a given coolant mass flow rate, thermal protection over the maximum surface area can be accomplished best by injecting the coolant flow through multiple slots.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Sept
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  • 68
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    Effect of compliant wall motion on turbulent boundary layers (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A critical analysis of available compliant wall data which indicated drag reduction under turbulent boundary layers is presented. Detailed structural dynamic calculations suggest that the surfaces responded in a resonant, rather than a compliant, manner. Alternate explanations are given for drag reductions observed in two classes of experiments: (1) flexible pipe flows and (2) water-backed membranes in air. Analysis indicates that the wall motion for the remaining data is typified by short wavelengths in agreement with the requirements of a possible compliant wall drag reduction mechanism recently suggested by Langley.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 69
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    An implicit-iterative solution of the heat conduction equation with a radiation boundary condition (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: For the problem of predicting one-dimensional heat transfer between conducting and radiating mediums by an implicit finite difference method, four different formulations were used to approximate the surface radiation boundary condition while retaining an implicit formulation for the interior temperature nodes. These formulations are an explicit boundary condition, a linearized boundary condition, an iterative boundary condition, and a semi-iterative boundary method. The results of these methods in predicting surface temperature on the space shuttle orbiter thermal protection system model under a variety of heating rates were compared. The iterative technique caused the surface temperature to be bounded at each step. While the linearized and explicit methods were generally more efficient, the iterative and semi-iterative techniques provided a realistic surface temperature response without requiring step size control techniques.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal for Numerical Methods in Engineering; 11; 10, 1; 1977
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  • 70
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    Wall cooling effects on hypersonic transitional/turbulent boundary layers at high Reynolds numbers (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The characteristics of a thick hypersonic boundary layer turbulent for a length of 175 cm on a 4 deg sharp wedge were measured. The resulting boundary layer was free from transverse curvature effects and only mildly affected by upstream history effects caused by pressure and wall temperature gradients. Heat-transfer distributions were used to locate regions of laminar, transitional, and turbulent flow at an edge unit Reynolds number of 470,000 cm at wall-to-total temperature ratios from about 0.3 to 1. Wall cooling had little effect on the location of the transition region. Pitot and total temperature profiles and skin-friction measurements were obtained at several locations along the model longitudinal centerline. Mixing length and turbulent Prandtl number distributions were derived from the fully turbulent mean profiles.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Oct. 197
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  • 71
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    Numerical turbulence modeling (1977)
    In:  CASI
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    Publication Date: 2012-05-19
    Description: The underlying bases and developments in two techniques of detailed turbulence modeling are described where the flow is treated in the Eulerian sense, and one technique where the Lagrangian motions of vortices are followed. First, a technique is described for solving the single-point statistically averaged conservation equations. The Reynolds stresses that appear in these equations are evaluated by solving supplemental differential equations which contain terms that are modeled. A sequence of increasingly complex, but also increasingly general, modeling equations is described and computations based on these equations are compared with experimental data. The hierarchy of models described terminates with equations for the individual components of the Reynolds stress tensor. The second Eulerian technique approach to turbulence modeling is the direct numerical simulation of turbulent fields. In this approach, all three dimensional eddies between a predetermined range of sizes are computed in time within a specified volume of flow. Present day computers require a tradeoff between the size of the volume that can be considered and the degree of resolution of the turbulent eddies. Techniques of modeling the smallest eddies are described that permit enlarging the volume, or Reynolds number, that can be considered.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Computational Fluid Dyn.; 37 p
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  • 72
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    Prediction of outer layer mixing lengths in turbulent boundary layers (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Predictions of mixing length by Pletcher's (1976) method (using a two-layer eddy viscosity model for a turbulent boundary layer at low Reynolds numbers) are compared to some values derived from turbulent boundary-layer profiles by other authors. The model is incorporated into a finite-difference scheme, to accurately predict low Reynolds number skin friction in supersonic flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 15; Apr. 197
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  • 73
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    Application of the method of integral relations to laminar boundary layers in three dimensions (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The method of integral relations is extended to general three-dimensional compressible laminar boundary layer flows. The transformation employed to transform the basic three-dimensional compressible boundary layer equations into quasi-incompressible form is an extension of the Howarth transformation. The resulting system of differential equations is integrated numerically by the method of integral relations as proposed by Dorodnitsyn. To demonstrate the accuracy of the method, it is applied to calculation of the parabolic flow over a flat plate and the boundary flow over an infinite yawed cylinder, for which solutions are known. It is then applied to the flow over a flat plate disturbed by a cylinder normal to the plate, for which a finite-difference solution is available for comparison. It is finally applied to calculating the crossflow velocity variation for supersonic flow over a swept wedge.
    Keywords: AERODYNAMICS
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  • 74
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    A novel concept for subsonic inlet boundary-layer control (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A self-bleeding method for boundary layer control is described and tested for a subsonic inlet designed to operate in the flowfield generated by high angles of attack. Naturally occurring surface static pressure gradients are used to remove the boundary layer from a separation-prone region of the inlet and to reinject it at a less critical location with a net performance gain. The results suggest that this self-bleeding method for boundary-layer control might be successfully applied to other inlets operating at extreme aerodynamic conditions.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; Apr. 197
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  • 75
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    Mach 6 flowfield survey at the engine inlet of a research airplane (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A flowfield survey was conducted to better define the nature of vehicle forebody flowfield at the inlet location of an airframe-integrated scramjet engine mounted on the lower surface of a high-speed research airplane to be air launched from a B-52 and rocket boosted to Mach 6. The tests were conducted on a 1/30-scale brass model in a Mach-6 20-in. wind tunnel at Reynolds number of 11,200,000 based on distance to engine inlet. Boundary layer profiles at five spanwise locations indicate that the boundary layer in the area of the forebody centerline is more than twice as thick as the boundary layer at three outboard stations. It is shown that the cold streak found in heating contours on the centerline of the forebody is caused by a thickening of the boundary layer on the centerline, and that this thickening decreases with angle of attack.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; Apr. 197
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  • 76
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    Hot-wire anemometry in transonic flow (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The use of hot-wire anemometry for obtaining fluctuating data in transonic flows has been evaluated. From hot-wire heat loss correlations based on previous transonic data, the sensitivity coefficients for velocity, density, and total temperature fluctuations have been calculated for a wide range of test conditions and sensor parameters. For sensor Reynolds number greater than 20 and high sensor overheat ratios, the velocity sensitivity remains independent of Mach number and equal to the density sensitivity. These conditions were verified by comparisons of predicted sensitivities with those from recent direct calibrations in transonic flows. Based on these results, techniques are presented to obtain meaningful measurements of fluctuating velocity, density, and Reynolds shear stress using hot-wire and hot-film anemometers. Example of these measurements are presented for two transonic boundary layers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 15; Mar. 197
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  • 77
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    A block iterative finite element algorithm for numerical solution of the steady-state, compressible Navier-Stokes equations (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An iterative method for numerically solving the time independent Navier-Stokes equations for viscous compressible flows is presented. The method is based upon partial application of the Gauss-Seidel principle in block form to the systems of the nonlinear algebraic equations which arise in construction of finite element (Galerkin) models approximating solutions of fluid dynamic problems. The continuous cubic element on triangles is employed for function approximation. Computational results for a free shear flow at Re = 1000 indicate significant achievement of economy in iterative convergence rate over finite element and finite difference models which employ the customary time dependent equations and symptotic time marching procedure to steady solution. Numerical results are in excellent agreement with those obtained for the same test problem employing time marching finite element and finite difference solution techniques.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal for Numerical Methods in Engineering; 11; 12, 1; 1977
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  • 78
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    Condensation heat transfer in rotating heat pipes in the presence of a non-condensable gas (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An analysis of condensation problems in rotating heat pipes containing vapors with different concentrations of non-condensable gases is given. In situations such as this, temperature and concentration gradients are set up in the vapor-gas mixture. There is a transport of mass due to temperature gradients accompanied by an energy transport phenomena due to a concentration gradient. A Nusselt type analysis is not suited to this type of problem; however, a boundary layer type approach has successfully been used to analyze stationary condensation systems with non-condensable gases present. The present boundary layer analysis is presented for condensation processes on the inside of a rotating heat pipe in the presence of non-condensable gases.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Revue Roumaine des Sciences Techniques; vol. 22
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  • 79
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    Comparison of numerical and experimental 'conical' flow fields in supersonic corners with compression and/or expansion (1977)
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    Publication Date: 2011-08-17
    Description: The flow field produced by the intersection of two plane solid surfaces in a supersonic stream is a complex interference flow. These flows can be fully compressive, fully expansive, or of mixed compression-expansion nature. This paper presents a comparison of the experimentally obtained flow-field structure in an axial corner with that predicted numerically by using a shock-capturing finite-difference method. The effect of sweep and surface deflection are evaluated, and the general influence of each is presented for the three classes of corner flow. The results show that the numerical method is a valuable aid in understanding the flow structure for simple configurations. In addition, confidence in the numerical method is gained for use in solving more general three-dimensional configurations where the flow is nonconical and several wave interaction may be presented.
    Keywords: AERODYNAMICS
    Type: British Aircraft Corp.
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  • 80
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    Unsteady flow in a supersonic cascade with strong in-passage shocks (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Linearized theory is used to study the unsteady flow in a supersonic cascade with in-passage shock waves. We use the Wiener-Hopf technique to obtain a closed-form analytical solution for the supersonic region. To obtain a solution for the rotational flow in the subsonic region we must solve an infinite set of linear algebraic equations. The analysis shows that it is possible to correlate quantitatively the oscillatory shock motion with the Kutta condition at the trailing edges of the blades. This feature allows us to account for the effect of shock motion on the stability of the cascade. Unlike the theory for a completely supersonic flow, the present study predicts the occurrence of supersonic bending flutter. It therefore provides a possible explanation for the bending flutter that has recently been detected in aircraft-engine compressors at higher blade loadings.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 83; Dec. 5
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  • 81
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    Correlation of turbulent shear layer attachment peak heating near Mach 6 (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A correlation of new turbulent two-dimensional data and peak heating data for attaching free shear layers is presented for a 2.54-cm and 5.08-cm diam cylindrical leading-edge slab 25.4 cm long, and 7.62 and 10.16 cm wide. A 30.48 x 25.4 cm sharp leading-edge flat plate set at 15 and 20 deg is used to generate plane impinging shocks. The freestream Mach number is 6 and the freestream Reynolds number varies from 3,300,000 to 25,600,000/m. Peak heating is measured on silica-based epoxy models with a phase change coating technique. A comparison of the free shear layer data with the transition data of Birch and Keyes (1972) reveals that the shear layer data are turbulent at attachment. The trend of the data shows that peak heating is strongly affected by the state of development at attachment. As the free shear layers become more fully developed, the data approach the two-dimensional correlation. Persistence of transitional flow structures for supersonic free shear flows is pointed out.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Dec. 197
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  • 82
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    How good is jet lift VTOL technology (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The status of technologies for jet-lift V/STOL aircraft is examined, and a critical review of the performance of jet-lift VTOL aircraft built to date is made. Most jet-lift aircraft have suffered from adverse propulsion-induced effects during takeoff and landing. Flight dynamics of jet-lift aircraft have suffered from shortcomings in static and dynamic stability, control characteristics, and flight path control. Some of the main problems to be considered during the selection of a propulsion system arrangement for a V/STOL fighter are discussed. At present, experimental and analytical data on supersonic V/STOL configurations are insufficient to permit evaluating propulsion system arrangements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 15; Dec. 197
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  • 83
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    Calculated heating on the afterbody nozzle of a hypersonic aircraft concept (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The present analysis was carried out to estimate the heating levels of the external nozzle of a scramjet/airframe-integrated research aircraft. A parametric examination of the effects of Mach number, reference length, and wall temperature showed that the heating rate distributions are independent of reference length and wall temperature. The initial heating rates obtained for a Mach 6 flight are in the (3 to 8) x 10 to the 5th power W/sq m range. Underlying the entire study is the question of nozzle boundary layer formation and growth, as well as the question of the reference length value that should be used in the computations. It is shown that the reference length is not the dominant factor setting the heating levels; an attempt to bound the actual length was made. A more detailed calculation of the rates requires further work to gain a better understanding of the combustor exit boundary layer.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; Dec. 197
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  • 84
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    Revised international representations for the viscosity of water and steam and new representations for the surface tension of water (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 85
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    Effect of endwall cooling on secondary flows in turbine stator vanes (1977)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: An experimental investigation was performed to determine the effect of endwall cooling on the secondary flow behavior and the aerodynamic performance of a coreturbine stator vane. The investigation was conducted in a cold-air, full-annular cascade, where three-dimensional effects could be obtained. Two endwall cooling configurations were tested. In the first configuration, the cooling holes were oriented so that the coolant was injected in line with the inviscid streamline direction. In the second configuration, the coolant was injected at an angle of 15 deg to the inviscid streamline direction and oriented toward the vane pressure surface. In both cases the stator vanes were solid and uncooled so that the effect of endwall cooling could be obtained directly. Total-pressure surveys were taken downstream of the stator vanes over a range of cooling flows at the design, mean-radius, critical velocity ratio of 0.778. Changes in the total-pressure contours downstream of the vanes were used to obtain the effect of endwall cooling on the secondary flows in the stator. Comparisons were made between the two cooled-endwall configurations and with the results obtained previously for solid endwalls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Secondary Flows in Turbomachines; 29 p
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  • 86
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    Monte Carlo turbulence simulation (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes turbulence simulation experiments based on the principles of control system theory, that is, the construction of a system characterized by a system function such that upon exciting the system with prescribed noise processes the output of the system is a realization of a random processing the desired statistical attributes of turbulence. An experimental autocorrelation of Jimsphere measurements of wind velocity was approximated to simulate turbulent wind. From the approximate autocorrelation function, the required system function is obtained, and a discrete time system is designed. Another method of simulation is to solve the convolution integral by filter techniques. Other methods include discrete Fourier simulation and self-similar simulation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 87
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    Turbulence processes and simple closure schemes (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The problem of closure in turbulence in the case of two-point correlations resides in the existence of two unknowns E and W, the energy spectrum function and the transfer function, respectively, in the spectrum equation. In the case of weak turbulence, W is negligible. In case of higher correlations, closure can be effective by neglecting the inertia term in the highest order term used. Specifying a certain number of spectra at an initial time is also a way of getting around the closure problem. A simple case of turbulent shear flow is then considered, where two-point correlation equations are used and the velocity is broken into mean and fluctuating components. This yields a differential equation for the energy spectrum, the three terms of which are the energy spectrum, production term and dissipation term. They are plotted for a particular time. Similar analyses and comparisons with experiment are made for pipe and boundary layer flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 88
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    Aerodynamic characteristics at high angles of attack (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An overview is presented of the aerodynamic inputs required for analysis of flight dynamics in the high-angle-of-attack regime wherein large-disturbance, nonlinear effects predominate. An outline of the presentation is presented. The discussion includes: (1) some important fundamental phenomena which determine to a large extent the aerodynamic characteristics of airplanes at high angles of attack; (2) static and dynamic aerodynamic characteristics near the stall; (3) aerodynamics of the spin; (4) test techniques used in stall/spin studies; (5) applications of aerodynamic data to problems in flight dynamics in the stall/spin area; and (6) the outlook for future research in the area.
    Keywords: AERODYNAMICS
    Type: Von Karman Inst. for Fluid Dyn. Aerodyn. Inputs for Probl. in Aircraft Dyn., Vol. 2; 39 p
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  • 89
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    Vortex attenuation flight experiments (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flight tests evaluating the effects of altered span loading, turbulence ingestion, combinations of mass and turbulence ingestion, and combinations of altered span loading turbulance ingestion on trailed wake vortex attenuation were conducted. Span loadings were altered in flight by varying the deflections of the inboard and outboard flaps on a B-747 aircraft. Turbulence ingestion was achieved in flight by mounting splines on a C-54G aircraft. Mass and turbulence ingestion was achieved in flight by varying the thrust on the B-747 aircraft. Combinations of altered span loading and turbulence ingestion were achieved in flight by installing a spoiler on a CV-990 aircraft and by deflecting the existing spoilers on a B-747 aircraft. The characteristics of the attenuated and unattenuated vortexes were determined by probing them with smaller aircraft. Acceptable separation distances for encounters with the attenuated and unattenuated vortexes are presented.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 369-403
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  • 90
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    Ground-based facilities for evaluating vortex minimization concepts (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: To determine the feasibility of altering the formation and decay of aircraft trailing vortexes through aerodynamic means, the test capabilities of two wind tunnels and two towing basins were used. The facilities, common models, and measurement techniques that were employed in the evaluation of vortex minimization concepts are described.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 129-156
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  • 91
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    Advanced low-NO(x) combustors for supersonic high-altitude gas turbines (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The impact of gas-turbine-engine-powered aircraft on worldwide pollution was defined within two major areas of contribution. First, the contribution of aircraft to the local air pollution of metropolitan areas and, second, the long-term effects on the chemical balance of the stratosphere of pollutants emitted from future generations of high-altitude, supersonic commercial and military aircraft. Preliminary findings indicate that stratospheric oxides of nitrogen (NOx) emissions may have to be limited to very low levels if, for example, ozone depletion with concomitant increases in sea-level radiation, are to be avoided. Theoretical considerations suggest that (NOx) levels as low as 1.0 gram per kilogram of fuel and less should be attainable from a idealized premixed type of combustor. Experimental rig studies were intended to explore new combustor concepts designed to minimize the formation of (NOx) in aircraft gas turbines and to define their major operational problems and limitations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 393-415
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  • 92
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    Soot formation in a turbulent swirling flow (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The qualitative understanding of soot formation in simple models of gas turbine primary-zone combustors is summarized. Soot formation in flame radiation and air pollution was investigated. Results are presented, namely: (1) if the fuel is premixed with air in approximately stoichiometric proportions, the sequence of states that a fluid element undergoes as it burns is quite different from the sequence when liquid or vapor fuel is injected into an air-flow; (2) swirling flows, as are typical or swirl-can combustors, when burning, can amplify small aerodynamic disturbances upstream of the swirl vanes; and (3) different fuels form significantly different amounts of soot. Each of these effects makes major changes in the amount of soot formed in a given combustor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 309-321
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  • 93
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    Pollution reduction technology program for turboprop engines (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The reduction of CO, HC, and smoke emissions while maintaining acceptable NO(x) emissions without affecting fuel consumption, durability, maintainability, and safety was accomplished. Component combustor concept screening directed toward the demonstration of advanced combustor technology required to meet the EPA exhaust emissions standards for class P2 turboprop engines was covered. The combustion system for the Allison 501-D22A engine was used, and three combustor design concepts - reverse flow, prechamber, and staged fuel were evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 125-147
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  • 94
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    Ceramic composite protection for turbine disc bursts (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ceramic composite turbine disc protection panels for the A300B were developed using armor technology. Analytical predictions for modifying the ballistic projectile armor system were verified by a test program conducted to qualify the rotor containment system. With only a slight change in the areal density of the armor system a more than two-fold increase in kinetic energy protection level was achieved. Thickness of the fiberglass reinforced plastic backing material was increased to achieve an optimum ratio of ceramic thickness to backing thickness for the different ballistic defeat condition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 277-293
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  • 95
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    Materials and manufacturing processes for increased life/reliability (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Improvements in both quality and durability of disk raw material for both military and commercial engines necessitated an entirely new concept in raw material process control which imposes careful selection, screening and sampling of the basic alloy ingredients, followed by careful monitoring of the melting parameters in all phases of the vacuum melting sequence. Special care is taken to preclude solidification conditions that produce adverse levels of segregation. Melt furnaces are routinely cleaned and inspected for contamination. Ingots are also cleaned and inspected before entering the final melt step.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 347-368
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  • 96
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    Numerical analysis of projectile impact in woven texile structures (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Computer codes were developed for simulating the dynamic fracture and viscoelastic constitutive response due to stress wave interaction and reflections caused by ballistic impact on woven textiles. The method, which was developed for use in the design and analysis of protection devices for personnel armor, has potential for use in studies of rotor blade burst containment at high velocity. Alterations in coding required for burst containment problems are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Assessment of Technol. for Turbojet Engine Rotor Failures; p 247-260
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  • 97
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    Lightweight engine containment (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Kevlar fabric styles and weaves were studied, as well as methods of application for advanced gas turbine engines. The Kevlar material was subjected to high speed impacts by simple projectiles fired from a rifle, as well as more complex shapes such as fan blades released from gas turbine rotors in a spin pit. Just contained data was developed for a variety of weave and/or application techniques, and a comparative containment weight efficiency was established for Kevlar containment applications. The data generated during these tests is being incorporated into an analytical design system so that blade containment trade-off studies between Kevlar and metal case engine structures can be made. Laboratory tests and engine environment tests were performed to determine the survivability of Kevlar in a gas turbine environment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 235-245
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  • 98
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    Approaches to rotor fragment protection (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Key airworthiness design criteria considerations for fragment protection as found in various FAA requirements in FAR Parts 25 and 33, and in interpretive 8110 orders are reviewed. The impact of providing aircraft armor in lieu of engine armor for typical three- and four-engine wide bodied transports for protection within the length of the engine case as well as from fragments exiting ahead of the enlet engine inlet flange is assessed. For protection within the length of the engine case, armor weight penalties, plus fuel burned and dollar cost of carrying the armor protection are defined. Immediately ahead of the inlet flange, direct tangential impacts are predominant, but further forward, rebound impacts predominate. Armor thickness requirements and fuel cost impact of protection are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 101-103
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  • 99
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    Engine Non-Containment: The UK CAA View (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Airworthiness accidents account for roughly one quarter of the total number of accidents to public transport turbojet aircraft. The most reliable, practicable, and cost-effective means of minimizing damage outside the confines of the nacelle is to make the aircraft design invulnerable to any debris which may affect the aircraft. A failure model was developed for use by aircraft builders in measuring the freedom from catastrophe factor of their design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 11-32
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  • 100
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    Evaluation of thermal soak times (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A mathematical model for the heat transfer within the electronics package of a Chaparral missile was performed. The Grashof number for this configuration was less than 2000 which indicated that the primary mode of heat transfer was conduction. The Vodicka theory for heat conduction in laminated composite media was utilized to obtain the solution for the model.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Goddard Space Flight Center Ninth Conf. on Space Simulation; p 435-441
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