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  • Other Sources  (2,213)
  • AERODYNAMICS  (2,093)
  • 42.75
  • Aircraft Design, Testing and Performance
  • Animals
  • Cell & Developmental Biology
  • Earth model, also for more shallow analyses !
  • 1980-1984  (2,148)
  • 1935-1939  (38)
  • 1930-1934  (27)
Collection
Years
Year
  • 1
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    In:  Phys. Earth Planet. Inter., Luxembourg, U.S. Geological Survey, vol. 25, no. 24, pp. 297-356, pp. B05309, (ISBN 0-471-26610-8)
    Publication Date: 1981
    Keywords: Seismology ; Earth model, also for more shallow analyses ! ; PREM ; PEPI ; Dziewonski
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  • 2
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    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 37-41, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: Gravimetry, Gravitation ; Earth model, also for more shallow analyses !
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  • 3
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    In:  Bull. Am. Meteor. Soc., Milano, Gustav Fischer, vol. 12, no. 3, pp. 207, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1931
    Keywords: Geothermics ; Meteorology ; Earth model, also for more shallow analyses !
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  • 4
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    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 65-66, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology
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  • 5
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 29, no. 6, pp. 531-538, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Physical properties of rocks ; BSSA
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  • 6
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    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 47, no. 3, pp. 306-307, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Tectonics ; CRUST ; Earth model, also for more shallow analyses ! ; Plate tectonics
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  • 7
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    In:  Rev. Geophys. Space Phys., Berlin, Schweizerbart'sche Verlagsbuchhandlung, vol. 21, no. 1-2, pp. 51-74, pp. L07302, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Publication Date: 1983
    Keywords: Review article ; Earth model, also for more shallow analyses ! ; Geochemistry ; Mineralogy ; Seismology
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  • 8
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    In:  Geophys. J. R. astr. Soc., Tulsa, 450 pp.; 2nd modified and expanded ed., Society of Exploration Geophysics, vol. 75, no. 1-4, pp. 779-838, pp. B12408, (ISSN: 1340-4202)
    Publication Date: 1983
    Keywords: Seismology ; Shear waves ; earth mantle ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; GJRaS
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  • 9
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    In:  J. Geophys. Res., Bonn, Inst. f. Theoret. Geodäsie, vol. 88, no. B1, pp. 10285-10298, pp. B01401, (ISSN: 1340-4202)
    Publication Date: 1983
    Keywords: Earth model, also for more shallow analyses ! ; (The Earth's free) oscillations ; NOModelling ; Low frequency ... ; JGR
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  • 10
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    In:  J. Geophys. Res., Tulsa, 450 pp.; 2nd modified and expanded ed., Society of Exploration Geophysics, vol. 88, no. 48, pp. 8145-8159, pp. B02405, (ISSN: 1340-4202)
    Publication Date: 1983
    Keywords: Reflectivity ; Mineralogy ; Seismology ; Earth model, also for more shallow analyses ! ; Geochemistry ; JGR
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  • 11
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    In:  Nature, Bonn, Inst. f. Theoret. Geodäsie, vol. 298, no. B1, pp. 609-613, pp. B01401, (ISSN: 1340-4202)
    Publication Date: 1982
    Keywords: Earth model, also for more shallow analyses ! ; Low frequency ... ; (The Earth's free) oscillations ; NOModelling
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  • 12
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    In:  Tectonophys., Tokyo, Railway Tech. Res. Inst., vol. 69, no. 1, pp. 1-35, pp. L09308, (ISSN: 1340-4202)
    Publication Date: 1980
    Keywords: Seismology ; Shear waves ; reflections ; Earth model, also for more shallow analyses !
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  • 13
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    In:  Nature, Amsterdam, Schweizerbart'sche Verlagsbuchhandlung, vol. 283, no. 8-9, pp. 343-346, pp. L07302, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Publication Date: 1980
    Keywords: Tectonics ; Fault zone ; Geol. aspects ; Earth model, also for more shallow analyses !
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  • 14
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    In:  J. Geophys. Res., Tulsa, 450 pp.; 2nd modified and expanded ed., Society of Exploration Geophysics, vol. 88, no. 1-4, pp. 8160-8170, pp. B12408, (ISSN: 1340-4202)
    Publication Date: 1983
    Keywords: Seismology ; Shear waves ; earth mantle ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; JGR
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  • 15
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    In:  Gerlands Beitr. zur Geophysik, Jena, Physica-Verlag, vol. 93, no. 1, pp. 323-325, pp. L24313, (ISSN: 1340-4202)
    Publication Date: 1984
    Keywords: Earth model, also for more shallow analyses ! ; Velocity analysis ; Seismic stratigraphy ; Stacking ; CRUST ; earth mantle
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  • 16
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    In:  Phil. Trans. Roy. Soc. London, Bonn, Inst. f. Theoret. Geodäsie, vol. A308, no. B1, pp. 479-522, pp. B01401, (ISSN: 1340-4202)
    Publication Date: 1982
    Keywords: Quality factor ; Rheology ; Low frequency ... ; Earth model, also for more shallow analyses ! ; Physical properties of rocks
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  • 17
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    In:  Bull. Seism. Soc. Am., Roma, Publicazioni dell'Istituto Nazionale di Geofisica, vol. 70, no. B4, pp. 691-716, pp. B04102, (ISBN: 0-12-018847-3)
    Publication Date: 1980
    Keywords: Synthetic seismograms ; Earth model, also for more shallow analyses ! ; Inhomogeneity ; BSSA
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  • 18
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    In:  J. Geophys. Res., London, Army Corps of Engineers, Woodward-Clyde Consultants, vol. 89, no. 5, pp. 6017-6040, pp. 1013, (ISBN: 0-12-018847-3)
    Publication Date: 1984
    Keywords: ConvolutionE ; Earth model, also for more shallow analyses ! ; Teleseismic events ; Seismology ; Deep seismic sounding (espec. cont. crust) ; Physical properties of rocks ; GeodesyY ; JGR
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  • 19
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    In:  Forschungen und Fortschritte, Milano, Gustav Fischer, vol. 6, no. 3, pp. 66-67, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: Earth model, also for more shallow analyses ! ; Geothermics ; Tectonics
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  • 20
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    In:  Forschungen und Fortschritte, Milano, Gustav Fischer, vol. 6, no. 3, pp. 133-135, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: Seismology ; Earth model, also for more shallow analyses ! ; Seismicity
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  • 21
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    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 156-157, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: Earth model, also for more shallow analyses ! ; CRUST ; earth mantle
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  • 22
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    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 158-160, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: Gravimetry, Gravitation ; Earth model, also for more shallow analyses !
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  • 23
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    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 50, no. 6, pp. 1950, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Physical properties of rocks
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  • 24
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    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 44, no. 3, pp. 170-171, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1933
    Keywords: CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; Velocity depth profile
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  • 25
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    In:  Annales Geophysicae, Padova, AGU, vol. 2, no. 2, pp. 137-138, pp. 1273, (ISSN: 1340-4202)
    Publication Date: 1984
    Keywords: Earth model, also for more shallow analyses ! ; Velocity depth profile ; Italy ; Greece ; Seismology
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  • 26
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    Am Geophys. Union
    In:  Washington, D. C., Am Geophys. Union, vol. 2, no. 22, pp. 662-664, (ISBN 0-470-87000-1 (HB), ISBN 0-470-87001-X (PB))
    Publication Date: 1981
    Keywords: Textbook of geophysics ; Earth model, also for more shallow analyses ! ; Plate tectonics
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  • 27
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    In:  Geophys. J. R. astr. Soc., Hannover, Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 79, no. 8, pp. 363-383, pp. L08305
    Publication Date: 1984
    Keywords: EUROPROBE (Geol. and Geophys. in eastern Europe) ; P-waves ; CRUST ; earth mantle ; Earth model, also for more shallow analyses ! ; Deep seismic sounding (espec. cont. crust) ; Babuska ; GJRaS
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  • 28
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    In:  J. Geophys. Res., Luxembourg, U.S. Geological Survey, vol. 89, no. 24, pp. 5929-5952, pp. B05309, (ISBN 0-471-26610-8)
    Publication Date: 1984
    Keywords: Seismology ; earth mantle ; Travel time ; Tomography ; Earth model, also for more shallow analyses ! ; Inversion ; JGR ; Dziewonski
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  • 29
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    In:  J. Geophys. Res., Bonn, Pergamon, vol. 85, no. 18, pp. 7183-7194, pp. 2018, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1980
    Keywords: Earth model, also for more shallow analyses ! ; Europe ; Asia ; Seismology ; JGR
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  • 30
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    In:  J. Geophys. Res., Warszawa, Icelandic Meteorological Office, Ministry for the Environment,, vol. 89, no. 4, pp. 11465-11475, pp. 2540, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1984
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; JGR
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  • 31
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    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 55, no. 3, pp. 373-374, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1931
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; Seismics (controlled source seismology)
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  • 32
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 185-246, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; BSSA
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  • 33
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    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 32, no. 3, pp. 87-94, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1931
    Keywords: Geothermics ; Earth model, also for more shallow analyses ! ; Meteorology
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  • 34
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 21, no. 3, pp. 216-223, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1931
    Keywords: earth mantle ; Earth model, also for more shallow analyses ! ; Seismology ; BSSA
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  • 35
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    In:  Science, Milano, Gustav Fischer, vol. 82, no. 3, pp. 52, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1935
    Keywords: Earth model, also for more shallow analyses ! ; Elasticity ; Geothermics ; Physical properties of rocks
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  • 36
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    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 47, no. 3, pp. 1587-1610, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Tectonics ; CRUST ; Earth model, also for more shallow analyses ! ; Plate tectonics
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  • 37
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    In:  Science, Milano, Gustav Fischer, vol. 90, no. 6, pp. 456-458, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Earth model, also for more shallow analyses !
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  • 38
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    In:  Geophys. J. R. astr. Soc., Warszawa, Icelandic Meteorological Office, Ministry for the Environment,, vol. 76, no. 4, pp. 399-438, pp. 2540, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1984
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; GJRaS
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  • 39
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    In:  Neue Jahrbücher f. Wissenschaft und Jugendbildung, Milano, Gustav Fischer, vol. 6, no. 3, pp. 393-408, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: CRUST ; Earth model, also for more shallow analyses !
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  • 40
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    In:  Journ. Wash. Acad. Sci., Milano, Gustav Fischer, vol. 20, no. 3, pp. 17-25, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1930
    Keywords: Earth model, also for more shallow analyses ! ; Geothermics ; Tectonics
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  • 41
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    In:  Geoelektrische und geothermische Modelle für inhomogene Medien und Anwendung in Suche, Erkundung und Geotektonik, Geodätische und geophysikalische Veröffentlichungen, Reihe III, Heft 47, Philadelphia, 4, vol. 74, no. 13, pp. 178-187, pp. 2061, (ISSN: 1340-4202)
    Publication Date: 1980
    Keywords: Geothermics ; Earth model, also for more shallow analyses ! ; Layers
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  • 42
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    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XI:, pp. 291-299, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; Hypocentral depth
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  • 43
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    Elsevier
    In:  Amsterdam, Elsevier, vol. 81A and 81B, no. 22, pp. 65-70, (1405101733, 336 p.)
    Publication Date: 1984
    Keywords: Textbook of geophysics ; Earth model, also for more shallow analyses !
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  • 44
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    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 2: Der Aufbau der Erde (finished), 15 + 1119 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 440-564, (ISBN: 3-540-23712-7)
    Publication Date: 1931
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; Review article
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  • 45
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    Gustav Fischer
    In:  Professional Paper, Handwörterbuch der Naturwissenschaften Bd. 3, Jena, Gustav Fischer, vol. 3, no. VIIa, pp. 762-774, (ISBN: 3-540-23712-7)
    Publication Date: 1933
    Keywords: Handbook of geophysics ; Earth model, also for more shallow analyses !
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  • 46
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    Plenum Press
    In:  Bull., Polar Proj. OP-O3A4, Proceeding of the Third Course of the International School of Applied Geophysics, New York, Plenum Press, vol. 65, no. XVI:, pp. 185-198, (ISBN: 3-540-23712-7)
    Publication Date: 1980
    Keywords: Seismics (controlled source seismology) ; Reflection seismics ; Earth model, also for more shallow analyses ! ; Review article
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  • 47
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    Institut für Meteorologie und Geophysik, Goethe-Univ. Frankfurt
    In:  Diplomarbeit, Rotterdam, Institut für Meteorologie und Geophysik, Goethe-Univ. Frankfurt, vol. 10, no. PL-TR-91-2281, pp. 5789-5795, (ISBN 3-933346-037)
    Publication Date: 1984
    Keywords: Earth model, also for more shallow analyses ! ; Travel time ; earth Core ; Amplitude ; Seismology ; Inhomogeneity ; Velocity depth profile
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  • 48
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    Nauka
    In:  report, Moscow, Nauka, vol. 10, no. EUR 13341 EN, pp. 444-453, (ISBN 0 08 042822 3)
    Publication Date: 1980
    Keywords: Review article ; Deep seismic sounding (espec. cont. crust) ; Earth model, also for more shallow analyses ! ; Seismics (controlled source seismology) ; EUROPROBE (Geol. and Geophys. in eastern Europe) ; BIBTEX?
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  • 49
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    Europ. Seismol. Comm.
    In:  Proc. of the 17th Assembly of the ESC, Oslo, Europ. Seismol. Comm., vol. 11, no. PS-IV.17, pp. 27
    Publication Date: 1980
    Keywords: Earth model, also for more shallow analyses ! ; Seismics (controlled source seismology) ; Seismology
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  • 50
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    In:  Phys. Earth Plan. Int., Houston, Akademie-Verlag, vol. 33, no. 11, pp. 45-55, pp. L08310, (ISSN: 1340-4202)
    Publication Date: 1983
    Keywords: Geothermics ; Earth model, also for more shallow analyses ! ; earth mantle ; Seismology ; discontinuity ; hot ; spot ; PEPI
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  • 51
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    Edward Arnold
    In:  London, Edward Arnold, vol. 70, pp. 158, (ISBN 3-9808780-0-7)
    Publication Date: 1982
    Keywords: Textbook of geophysics ; Earth model, also for more shallow analyses ! ; Tectonics ; Plate tectonics ; Modelling ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; GeodesyY ; Seismology ; Finite Element Method
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  • 52
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    McGraw-Hill
    In:  New York, 10 + 413 pp.,, McGraw-Hill, vol. 7, no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Handbook of geophysics
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  • 53
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    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. I:, pp. 3-10, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Review article
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  • 54
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    McGraw-Hill
    In:  New York, 10 + 413 pp., 1st ed., McGraw-Hill, vol. 7, no. XII:, pp. 301-327, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: CRUST ; Earth model, also for more shallow analyses !
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  • 55
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    In:  J. Geophys. Res., Köln, Elsevier, vol. 89, no. 4, pp. 5953-5986, pp. 1015, (ISSN: 1340-4202)
    Publication Date: 1984
    Keywords: Seismology ; Tomography ; Surface waves ; Shear waves ; Inversion ; Earth model, also for more shallow analyses ! ; earth mantle ; JGR ; Dziewonski
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  • 56
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    Italian Physical Society and North-Holland Publ. Co.
    In:  Bologna and Amsterdam, 649 pp., Italian Physical Society and North-Holland Publ. Co., vol. LXXVIII, no. 2, pp. 125-169, (ISBN 0-521-00098-X)
    Publication Date: 1980
    Keywords: Textbook of geophysics ; Stress ; Lithosphere ; Seismology ; Geothermics ; Earth model, also for more shallow analyses ! ; Geomagnetics ; (The Earth's free) oscillations ; Inelastic ; Attenuation ; Rheology ; earth Core ; ConvolutionE ; Dziewonski
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  • 57
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    Am. Geophys. Union
    In:  Washington D. C., Am. Geophys. Union, vol. 3, no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Publication Date: 1981
    Keywords: Dynamic ; Geol. aspects ; Earth model, also for more shallow analyses ! ; Plate tectonics
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  • 58
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    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. VIII:, pp. 165-175, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; CRUST ; Crustal deformation (cf. Earthquake precursor: deformation or strain)
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  • 59
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    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. IX:, pp. 177-217, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; CRUST
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  • 60
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    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XIV:, pp. 345-360, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Elasticity
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  • 61
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    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XV:, pp. 361-384, (ISBN 0-12-305355-2)
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Stress ; Strength ; Elasticity ; Inelastic
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  • 62
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    Universität Frankfurt/Main
    In:  Berichte des Instituts für Meteorologie und Geophysik, Universität Frankfurt/Main, Universität Frankfurt/Main, vol. 1034, no. 53, pp. 206, (ISBN 3-933346-037)
    Publication Date: 1983
    Keywords: Rock mechanics ; Tectonics ; Earth model, also for more shallow analyses ! ; Velocity analysis ; Electromagnetic methods/phenomena ; Elasticity ; Physical properties of rocks ; earth mantle
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  • 63
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    University of California
    In:  Ph.D. Thesis, Berkeley, University of California, vol. C 560, 183 pp., no. 89-0684, 26 pp., pp. 1143-1146 (SL3.8), (ISBN 3-933346-037)
    Publication Date: 1984
    Keywords: Seismology ; earth Core ; SKS ; SKKS ; Travel time ; Earth model, also for more shallow analyses ! ; Velocity depth profile
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  • 64
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    Universität Karlsruhe
    In:  Dissertation, Grenoble, Universität Karlsruhe, vol. 10, no. GL-TR-89-0230, pp. 95-134, (ISBN 3-933346-037)
    Publication Date: 1981
    Keywords: Seismology ; PKP ; earth Core ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; Synthetic seismograms ; Transformations ; Hage
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  • 65
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    Toronto University Press
    In:  Proceedings of the 5th Pacific Science Congress, Victoria and Vancouver, B.C., Canada 1933, vol. 3, Toronto, Toronto University Press, vol. 10, no. GL-TR-89-0230, pp. 2511-2522, (ISBN 3-933346-037)
    Publication Date: 1934
    Keywords: CRUST ; Seismology ; Earth model, also for more shallow analyses ! ; Velocity depth profile
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  • 66
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    Inst. f. Meteorol. und Geophys.
    In:  Dissertation, Berichte, Universität Frankfurt/Main, Inst. f. Meteorol. und Geophys., vol. 1034, no. 41, pp. 206, (ISBN 3-933346-037)
    Publication Date: 1980
    Keywords: ConvolutionE ; Modelling ; Earth model, also for more shallow analyses ! ; earth mantle ; Rheology
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  • 67
    Publication Date: 2011-10-14
    Description: The test capabilities of the Stability Wind Tunnel of the Virginia Polytechnic Institute and State University are described, and calibrations for curved and rolling flow techniques are given. Oscillatory snaking tests to determine pure yawing derivatives are considered. Representative aerodynamic data obtained for a current fighter configuration using the curved and rolling flow techniques are presented. The application of dynamic derivatives obtained in such tests to the analysis of airplane motions in general, and to high angle of attack flight conditions in particular, is discussed.
    Keywords: AERODYNAMICS
    Type: AGARD Dyn. Stability Parameters; 13 p
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  • 68
    Publication Date: 2004-12-03
    Description: Projections of technological advances to the year 2000 have suggested a number of possible conceptual types of air vehicles. For convenience, these have been grouped according to speed, increasing from below Mach 1 (including hovering flight) through various Mach ranges to orbital flight. The potential performance capabilities that could be realized for each of these types of aircraft provide exciting prospects for the years beyond 2000. It is clear that the greater design flexibilities provided by the projected technology advances will permit significant improvements in performance, economy, and safety and allow the design and development of aircraft systems that current technology will not support. In the following sections, each vehicle type is discussed, noting design features and significant advances. Where related aircraft exist, the significant economic and performance factors are compared. In addition, for each concept, the technology developments considered essential for the advanced concept are identified. The types of aircraft described are examples of what advances in the technology projected for the year 2000 could provide. They are by no means all that would be possible. The panel's views on the current state of knowledge of systems intergration as a discipline and the need for advancement in this area presented in the concluding section of this report.
    Keywords: Aircraft Design, Testing and Performance
    Type: Aeronautics Technology Possibilities for 2000: Report of a Workshop; 195-213; NASA-CR-205283
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  • 69
    Publication Date: 2004-12-03
    Description: Over the last 50 years, aeronautical structures have evolved from the wood, fabric, and wire of low-speed biplanes to supersonic aircraft fabricated with advanced metallic and nonmetallic materials. The advances made in structures technology have had significant impact on aircraft design and performance. An example is the large weight reductions being realized from the utilization of composite materials for secondary and primary structures. However, structural advances have been evolutionary, not revolutionary. Through the year 2000, there are opportunities to obtain significant new advancements in structural technology. These advances could result in considerable performance and capability payoffs such as increased payload, range, speed, maneuverability, fuel efficiency, and safety through reductions in weight, increases in strength, and the ability to make structures pliable. Also, with new manufacturing processes it is possible that reductions in production costs will be realized. Some of the structural technology areas where future major advances could be made are adaptive structures, thermal structures, damage tolerant structures, propulsion system structures, and new structural concepts.
    Keywords: Aircraft Design, Testing and Performance
    Type: Aeronautics Technology Possibilities for 2000: Report of a Workshop; 71-98; NASA-CR-205283
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  • 70
    Publication Date: 2006-02-14
    Description: A KC-135A aircraft equipped with wing tip winglets was flight tested to demonstrate and validate the potential performance gain of the winglet concept as predicted from analytical and wind tunnel data. Flight data were obtained at cruise conditions for Mach numbers of 0.70, 0.75, and 0.80 at a nominal altitude of 36,000 ft. and winglet configurations of 15 deg cant/-4 deg incidence, 0 deg cant/-4 deg incidence, and baseline. For the Mach numbers tested the data show that the addition of winglets did not affect the lifting characteristics of the wing. However, both winglet configurations showed a drag reduction over the baseline configuration, with the best winglet configuration being the 15 deg cant/-4 deg incidence configuration. This drag reduction due to winglets also increased with increasing lift coefficient. It was also shown that a small difference exists between the 15 deg cant/-4 deg incidence flight and wind tunnel predicted data. This difference was attributed to the pillowing of the winglet skins in flight which would decrease the winglet performance.
    Keywords: AERODYNAMICS
    Type: KC-135 Winglet Program Rev.; p 103-116
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  • 71
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    In:  CASI
    Publication Date: 2006-02-14
    Description: A joint NASA/USAF program was conducted to accomplish the following objectives: (1) evaluate the benefits that could be achieved from the application of winglets to KC-135 aircraft; and (2) determine the ability of wind tunnel tests and analytical analysis to predict winglet characteristics. The program included wind-tunnel development of a test winglet configuration; analytical predictions of the changes to the aircraft resulting from the application of the test winglet; and finally, flight tests of the developed configuration. Pressure distribution, loads, stability and control, buffet, fuel mileage, and flutter data were obtained to fulfill the objectives of the program.
    Keywords: AERODYNAMICS
    Type: KC-135 Winglet Program Rev.; p 1-46
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  • 72
    Publication Date: 2006-02-14
    Description: A full-scale winglet flight test on a KC-135 airplane with an upper winglet was conducted. Data were taken at Mach numbers from 0.70 to 0.82 at altitudes from 34,000 feet to 39,000 feet at stabilized flight conditions for wing/winglet configurations of basic wing tip, 15/-4 deg, 15/-2 deg, and 0/-4 deg winglet cant/incidence. An analysis of selected pressure distribution and data showed that with the basic wing tip, the flight and wind tunnel wing pressure distribution data showed good agreement. With winglets installed, the effects on the wing pressure distribution were mainly near the tip. Also, the flight and wind tunnel winglet pressure distributions had some significant differences primarily due to the oilcanning in flight. However, in general, the agreement was good. For the winglet cant and incidence configuration presented, the incidence had the largest effect on the winglet pressure distributions. The incremental flight wing deflection data showed that the semispan wind tunnel model did a reasonable job of simulating the aeroelastic effects at the wing tip. The flight loads data showed good agreement with predictions at the design point and also substantiated the predicted structural penalty (load increase) of the 15 deg cant/-2 deg incidence winglet configuration.
    Keywords: AERODYNAMICS
    Type: KC-135 Winglet Program Rev.; p 47-102
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  • 73
    Publication Date: 2006-02-14
    Description: A joint NASA/U.S. industry program to test advanced technology airfoils in the Langley 0.3-meter Transonic Tunnel (TCT) was formulated under the Langley ACEE Project Office. The objectives include providing U.S. industry an opportunity to compare their most advanced airfoils to the latest NASA designs by means of high Reynolds number tests in the same facility. At the same time, industry would again experience in the design and construction of cryogenic test techniques. The status and details of the test program are presented. Typical aerodynamic results obtained, to date, are presented at chord Reynolds number up to 45 x 10(6) and are compared to results from other facilities and theory. Details of a joint agreement between NASA and the Deutsche Forschungs- und Versuchsantalt fur Luft- and Raumfahrt e.V. (DFVLR) for tests of two airfoils are also included. Results of these tests will be made available as soon as practical.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 37-53
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  • 74
    Publication Date: 2006-02-14
    Description: Dynamic model verification is the process whereby an analytical model of a dynamic system is compared with experimental data, adjusted if necessary to bring it into agreement with the data, and then qualified for future use in predicting system response in a different dynamic environment. These are various ways to conduct model verification. The approach taken here employs Bayesian statistical parameter estimation. Unlike curve fitting, whose objective is to minimize the difference between some analytical function and a given quantity of test data (or curve), Bayesian estimation attempts also to minimize the difference between the parameter values of that funciton (the model) and their initial estimates, in a least squares sense. The objectives of dynamic model verification, therefore, are to produce a model which: (1) is in agreement with test data; (2) will assist in the interpretation of test data; (3) can be used to help verify a design; (4) will reliably predict performance; and (5) in the case of space structures, will facilitate dynamic control.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 15 p
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  • 75
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    In:  CASI
    Publication Date: 2006-02-14
    Description: Multidisciplinary analysis often requires optimization of nonlinear systems that are subject to constraints. Trajectory optimization is one example of this situation. The Program to Optimize Simulated Trajectories (POST) was used successfully for a number of problems. The purpose is to describe POST and a new optimization approach that has been incorporated into it. Typical uses of POST will also be illustrated. The projected-gradient approach to optimization is the preferred option in POST and is discussed. A new approach to optimization, the random-walk approach, is described, and results with the random-walk approach are presented.
    Keywords: AERODYNAMICS
    Type: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 23 p
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  • 76
    Publication Date: 2006-02-14
    Description: The purpose is not to provide a detailed discussion of several wall interference experiments, but rather to use these experiments (recently accomplished in the Boeing Transonic Wind Tunnel (BTWT) to illustrate the problems associated with many of the measurements required by current wall interference assessment/correction (WIAC) procedures. The wall correction to lift is emphasized. It is shown that, because conventional tunnels and relatively small models continue to be used, the flow field or flow boundary measurements to be made impose severe requirements on the experiment itself. In some cases, existing instrumentation and test techniques may not be adequate to obtain the data accuracies needed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 21-42
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  • 77
    Publication Date: 2006-02-14
    Description: Based upon limited, initial observations of wall interference corrections obtained for one airfoil test, there is a need for assessing the upstream flow direction. If there is no direct measurement then a two-pass correction procedure similar to the one described here is required. Questions have arisen pertaining to the correct interpretation of the pressure coefficients measured on the slats of a slotted tunnel wall, the interpretation of just what the calculated equivalent body encompasses or should include, and what can or should be considered as quantitative criteria for data correctability. Further studies using this modified procedure will address these questions. Hopefully, a meaningful WIAC procedure can be validated for the airfoil tests in the 0.3-m TCT.
    Keywords: AERODYNAMICS
    Type: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 393-414
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  • 78
    Publication Date: 2006-02-14
    Description: A series of airfoils were tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT) at Reynolds numbers from 2 to 50 million. The 0.3-m TCT is equipped with Barnwell slots designed to minimize blockage due to the tunnel flow and ceiling. This design suggests that sidewall corrections for blockage is needed, and that a lifting airfoil produces a change in angle of attack. Sidewall correction methods were developed for subsonic and subsonic-transonic flow. Comparisons of theory with experimental data obtained in the 0.3-m TCT for two airfoils, the British NPL 9510 and the German R-4 are presented. The NPL 9510 was tested as part of the NASA/United Kingdom Joint Aeronautical Program and R-4 was tested as part f the DFVLR/NASA Advanced Airfoil Research Program. For the NPL 9510 airfoil, only those test points that one would anticipate being difficult to predict theoretically are presented.
    Keywords: AERODYNAMICS
    Type: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 375-392
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  • 79
    Publication Date: 2006-02-14
    Description: Representation of the flow around full-scale ships was sought in the subsonic wind tunnels in order to a Hain Reynolds numbers as high as possible. As part of the quest to attain the largest possible Reynolds number, large models with high blockage are used which result in significant wall interference effects. Some experiences with such a high blockage model tested in the NASA Ames 12-foot pressure wind tunnel are summarized. The main results of the experiment relating to wind tunnel wall interference effects are also presented.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 345-360
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  • 80
    Publication Date: 2006-02-14
    Description: The various procedures referred to as wall interference assessment and correction procedures presume the existence of a surface distribution of data (usually static pressure) measured over a surface on or near the tunnel walls for each test point to be assessed. An alternative approach in which a reasonably sophisticated computer model of the test section flow would be fitted parametrically to a sparse set of measured data is presented. The measurements provides line distributions of static pressure near the center lines of the top, side and bottom walls. The development of a test section model incorporating explicit recognition of discrete slots of finite length with controlled flow reentry into the solid wall downstream portion of the tunnel is shown.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 323-334
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  • 81
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    In:  CASI
    Publication Date: 2006-02-14
    Description: Wall interference is made predominant in tunnel models and by wall geometries to facilitate the study of slot flow. The viscous effects in slots are studied by two dimensional measurements of flow. Wall interference is assessed by measuring pressure distributions at two levels near the walls. Interference on lifting delta wings is calculated. Pressure distributions at inner boundaries show basis axisymetries between the pressure side and the suction side, pointing to the necessity of having wider slots on the pressure side.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 293-300
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  • 82
    Publication Date: 2006-02-14
    Description: Classical methods for calculation of wall corrections which are not satisfactory for a number of flows of interest are discussed. To meet these objections, a number of methods were developed which use measurements of the low at or close to the tunnel walls as an outer boundary condition to define wall interference. The development, assessment and application of one such method is summarized.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 259-271
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  • 83
    Publication Date: 2006-02-14
    Description: Measured field data as a boundary condition for calculating the interference flow field were applied. They are divided into two categories. In the first category, the field data must consist of distributions of a single velocity component, and an accurate estimate of the hypothetical free air contribution of the model to this component is required. The differences between measured values and estimated model contributions are attributed to wall interference and they establish the boundary condition. The associated field data measurements are simple, yet the necessary model representation generally is a serious drawback. The second category requires field data which consist of velocity vector distributions at the price of multicomponent measurements, but at the profit that no information at all is required about the model. In solid wall test sections, the price is reduced to virtually zero but the profit remains.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 221-229
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  • 84
    Publication Date: 2006-02-14
    Description: A limited-zone ventilated wall panel was developed for a closed-wall icing tunnel which permitted correct simulation of transonic flow over model rotor airfoil sections with and without ice accretions. Candidate porous panels were tested in the Ohio State University 6- x 12-inch transonic airfoil tunnel and result in essentially interference-free flow, as evidenced by pressure distributions over a NACA 0012 airfoil for Mach numbers up to 0.75. Application to the NRC 12- x 12-inch icing tunnel showed a similar result, which allowed proper transonic flow simulation in that tunnel over its full speed range.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 165-170
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  • 85
    Publication Date: 2006-02-14
    Description: The free-stream interference caused by the flow through the slotted walls of the test sections of transonic wind tunnels has continuously a problem in transonic tunnel testing. The adaptive-wall transonic tunnel is designed to actively control the near-wall boundary conditions by sucking or blowing through the wall. In order to make the adaptive-wall concept work, parameters for computational boundary conditions must be known. These parameters must be measured with sufficient accuracy to allow numerical convergence of the flow field computations and must be measured in an inviscid region away from the model that is placed inside the wind tunnel. The near-wall flow field was mapped in detail using a five-port cone probe that was traversed in a plane transverse to the free-stream flow. The initial experiments were made using a single slot and recent measurements used multiple slots, all with the tunnel empty. The projection of the flow field velocity vectors on the transverse plane revealed the presence of a vortex-like flow with vorticity in the free stream. The current research involves the measurement of the flow field above a multislotted system with segmented plenums behind it, in which the flow is controlled through several plenums simultaneously. This system would be used to control a three-dimensional flow field.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 119-142
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  • 86
    Publication Date: 2006-02-14
    Description: A three-dimensional adaptive-wall wind tunnel experiment was conducted at Ames Research Center. This experiment demonstrated the effects of wall interference on the upwash distribution on an imaginary surface surrounding a lifting wing. This presentation demonstrates how the interference assessment procedure used in the adaptive-wall experiments to determine the wall adjustments can be used to separately assess lift- and blockage-induced wall interference in a passive-wall wind tunnel. The effects of lift interference on the upwash distribution and on the model lift coefficient are interpreted by a simple horseshoe vortex analysis.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 89-100
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  • 87
    Publication Date: 2006-02-14
    Description: A wall interference correction method for closed rectangular test sections was developed which uses measured wall pressures. Measurements with circular discs for blockage and a rectangular wing as a lift generator in a square closed test section validate this method. These measurements are intended to be a basis of comparison for measurements in the same tunnel using ventilated (in these case, slotted) walls. Using the vortex lattice method and homogeneous boundary conditions, calculations were performed which show sufficiently high pressure levels at the walls for correction purposes in test sections with porous walls. In Gottingen, an adaptive test section (which is a deformable rubber tube of 800 mm diameter) was built and a computer program was developed which is able to find the necessary wall adaptation for interference-free measurements in a single step. To check the program prior to the first run, the vortex lattice method was used to calculate wall pressure distributions in the nonadapted test section as input data for the one-step method. Comparison of the pressure distribution in the adapted test section with free-flight data shows nearly perfect agreement. An extension of the computer program can be made to evaluate the remaining interference corrections.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 61-78
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  • 88
    Publication Date: 2006-02-14
    Description: The following areas were addressed: interchangeable test sections in the 0.3-M Transonic Cryogenic Tunnel (TCT); typical airfoil installation; airfoil capability; advanced technology airfoil test (ATAT); effects of the Reynolds number on the normal force coefficient; effects of the Reynolds number on the drag coefficient; and comparison of experimental results with theory.
    Keywords: AERODYNAMICS
    Type: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 361-374
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  • 89
    Publication Date: 2006-02-14
    Description: A formula for the determination of equivalent model geometry with two variables measured at the interface is derived, based on two dimensional subsonic flow. This predicted model profile is a reasonable initial estimate for transonic flow as long as the sonic region does not reach the interface. A general formula is given in two forms. One is in terms of complex variable functions and the other is an integral equation. The complex-function formula has the advantage of using analytic expressions. The integral equation form requires a numerical solution after assuming the model geometry as a polynomial function. Examples are given to illustrate the application of the formulas.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 335-342
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  • 90
    Publication Date: 2006-02-14
    Description: The two body problem was analyzed with a specific drag model. The model treats drag as a force proportional to the vector velocity and inversely proportional to the distance to the center of attraction. The solution is expressed in terms of known functions and is of a simple and compact form. The time of flight is expressed as a quadrature in the true anomaly. The results are: (1) development of a vector differential equation which allows analysis of an infinite number of gravitational and drag models; and (2) obtaining the solution of a linear differential equation using the inverse method of laplace transforms.
    Keywords: AERODYNAMICS
    Type: Houston Univ. The 1981 NASA ASEE Summer Fac. Fellowship Program, Vol. 2; 22 p
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  • 91
    Publication Date: 2006-02-14
    Description: Wall interference correction procedures seek to determine the required changes in certain flow or geometric parameters so that the difference between the flow properties at the model's surface in the tunnel and free air are minimized. A transonic and a linear correction procedure were developed for aircraft models. In addition to Mach number and angle of attack corrections, an estimate of the accuracy of the corrections is provided by the transonic correction procedure. Lift, pitching moment and pressure measurements near the tunnel walls are required. The efficiency and accuracy of the correction procedure are improved. Moreover, correction of both the wing and tail angles of attack is allowed. The procedure is valid for transonic as well as subcritical flows. However, for subcritical flows further approximations and simplifying assumptions are made, leading to a very simple and efficient correction procedure.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 301-322
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  • 92
    Publication Date: 2006-02-14
    Description: A facet of a unified tunnel correction scheme which uses wall pressures to determine tunnel induced blockage and upwash is described. With this method, there is usually no need to use data concerning model forces or power settings to find the interference; it follows directly from the pressures and tunnel dimensions. However, highly inclined jets do not produce good pressure signatures and are highly three dimensional, so they must be treated differently. Flow modeling is also discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 273-290
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  • 93
    Publication Date: 2006-02-14
    Description: Wall corrections as a function of wall porosity in the transonic wall interference problem was assessed. Effective porosities primarily for the two dimensional case were established as follows: (1) comparison of experimental data for two geometrically similar models of different chord/height ratio, an overall value of wall porosity could be deduced; (2) theoretical development which allows for unequal porosity for the floor and ceiling and wall boundary pressure measurements, porosities for floor and ceiling could be deduced; (3) a scheme was developed which allowed unequal porosity of floor and ceiling and streamwise varying porosity. The boundary layer development along the perforated floor and ceiling under the influence of the model pressure field, variations in boundary layer thickness underlining the difficulties in deducing meaningful values of wall porosity were determined. Wall boundary pressure measurement, in combination with singularity modelling of the airfoil, was sufficient to yield required information on the wall interference flow without having to establish some value for wall porosity. The singularity modelling of the airfoil initially covered only lift and volume but was extended to include drag and pitching moment, and second order volume term. It is shown by asymptotic transonic small disturbance analysis, that the derived corrections to angle of attack and free stream Mach number are correct to the first order.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 231-257
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  • 94
    Publication Date: 2006-02-14
    Description: The effort to develop classical methods to compute wall interference at transonic speeds is outlined. The two-dimensional theory and three-dimensional development are discussed. Also, some numerical application of the two-dimensional work are indicated. The basic advantages of the asymptotic theory are noted.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 193-203
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  • 95
    Publication Date: 2006-02-14
    Description: A solution for the tunnel wall boundary layer effects for three-dimensional subsonic tunnels is presented. The model potentials are represented with simple singularities placed on the centerline of the tunnel and Laplace's equation in cylindrical coordinates is solved for either the conventional homogeneous slotted-wall boundary condition, the solid-wall viscous boundary condition, or a combination of them. The most pronounced wall boundary layer effect is on solid blockage for completely closed wind tunnels. Boundary layers on the wall reduce the blockage from the solid-wall, no-boundary-layer case in a manner similar to opening slots in a solid wall. Additionally, for solid-wall tunnel configurations, the streamline curvature interference factor is reduced by a significant amount, whereas the lift interference factor at the model station does not depend on the boundary layer parameter. For combination wall configurations, the slot effect of the horizontal walls dominates the viscous effect of the solid sidewalls.
    Keywords: AERODYNAMICS
    Type: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 205-218
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  • 96
    Publication Date: 2006-02-14
    Description: Three experiments suitable for wall interference assessment and evaluation of proposed correction methods are presented. The experiments are: (1) a series of airfoil tests using a newly designed transonic flow facility that employs side-wall boundary layer suction and upper- and lower-wall shaping; (2) tests on a swept airfoil section spanning a solid-wall wind tunnel with fixed contouring on all four walls; and (3) tests on a swept wing of aspect ratio 3 mounted in a solid-wall wind tunnel with fixed flat walls. Each of the experiments provides data on the airfoil sections as well as on the wind tunnel walls. All the experiments were performed in solid wall wind tunnels corrected for boundary layer displacement effects. Although the experiments were performed primarily to evaluate computer code performance, it is believed that they also provide information that can be used to evaluate methods for assessing and correcting wall interference effects.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 171-190
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  • 97
    Publication Date: 2006-02-14
    Description: Sidewall boundary layer effects were investigated by applying partial upstream sidewall boundary layer removal in the Langley 0.3-m transonic cryogenic tunnel. Over the range of sidewall boundary layer displacement thickness of these tests the influence on pressure distribution was found to be small for subcritical conditions; however, for supercritical conditions the shock position was affected by the sidewall boundary layer. For these tests (with and without boundary layer remove) comparisons with predictions of the GRUMFOIL computer code indicated that Mach number corrections due to the sidewall boundary layer improve the agreement for both subcritical and supercritical conditions. The results also show that sidewall boundary layer removal reduces the magnitude of the sidewall correction; however, a suitable correction must still be made.
    Keywords: AERODYNAMICS
    Type: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 143-163
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  • 98
    Publication Date: 2006-02-14
    Description: A validation of a measured boundary condition technique was carried out to demonstrate the feasibility of a wall interference assessment/correction (WIAC) system. An experimental evaluation was also carried out to compare performances of various techniques, to define the number of necessary boundary measurements for accurate assessment/corrections and to define the envelope of test conditions for which accurate assessment/corrections are achieved. The relative merits of a WIAC system and an adaptive wall tunnel are compared. The measurement surface boundary data is performed with a system of two rotating pipes. These pipes sweep out a cylindrical measurement surface near the tunnel walls, approximately one inch from the wall at the closest point. The experimental model was specially designed and fabricated for the adaptive wall experiments. The model is a wing/tail/body configuration with swept lifting surface. The boundary data taken in Tunnel 1T with the rotating pipe system has been shown to offer several attractive features for WIAC code evaluation. Good spatial resolution of measurements is achieved and measurements are made upstream and downstream of the model. Also, two velocity components are determined.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 101-118
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  • 99
    Publication Date: 2006-02-14
    Description: The research undertaken concerning the computation and/or reduction of wall interference follows two main axes: improvement of wall correction determinations, and use of adaptive flexible walls. The use of wall-measured data to compute interference effects is reliable when the model representation is assessed by signatures with known boundary conditions. When the computed interferences are not easily applicable to correcting the results (especially for gradients in two-dimensional cases), the flexible adaptive walls in operation in T2 are an efficient and assessed means of reducing the boundary effects to a negligible level, if the direction and speed of the flow are accurately measured on the boundary. The extension of the use of adaptive walls to three-dimensional cases may be attempted since the residual corrections are assumed to be small and are computable.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 43-60
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  • 100
    Publication Date: 2006-02-14
    Description: To determine the low speed performance characteristics of a representative high aspect ratio supercritical wing, two low speed jet transport models were fabricated. A 12-ft. span model was used for low Reynolds number tests in the Langley 4- by 7-Meter Tunnel and the second, a 7.5-ft. span model, was used for high Reynolds number tests in the Ames 12-foot Pressure Tunnel. A brief summary of the results of the tests of these two models is presented and comparisons are made between the data obtained on these two models and other similar models. Follow-on two and three dimensional research efforts related to the EET high-lift configurations are also presented and discussed.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 55-77
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