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  • Other Sources  (3,598)
  • AERODYNAMICS  (3,000)
  • Aerodynamics
  • Aircraft Stability and Control
  • Cell & Developmental Biology
  • General Chemistry
  • Limnology
  • Seismicity
  • 1985-1989  (3,222)
  • 1945-1949  (263)
  • 1940-1944  (107)
  • 1920-1924
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Year
  • 1
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    A reinterpretation of the precursory seismic b-value anomaly from fracture mechanics (1989)
    In:  Geophys. J. RAS, DGG and EGS, San Francisco, Pergamon, vol. 96, no. B3, pp. 131-138, pp. 1447, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Fracture ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    A comparison of the spatio-temporal distribution of moment release for the 1986 Andreanof Islands earthquake with relocated seismicity (1989)
    In:  Geophys. Res. Lett., Berlin, Ges. f. Geowissenschaften e.V., vol. 16, no. 5454, pp. 1421-1424, pp. L02309, (ISSN 0343-5164)
    Details
    Publication Date: 1989
    Keywords: Earthquake ; Seismicity ; seismic Moment ; GRL
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Application of catastrophe theory in earthquake hazard assessment and earthquake prediction research (1989)
    In:  Tectonophys., L'wiw, Inst. f. Theoret. Geodäsie, vol. 167, no. 2-4, pp. 179-186, pp. B01408, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Earthquake precursor: prediction research ; Earthquake hazard ; Seismicity ; time ; fluctuations ; Earthquake precursor: statistical anal. of seismicity ; Thom ; 1972 ; FROTH ; (abstract)
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Theoretical calculations of the seismicity in Oaxaca, Mexico (1989)
    In:  Tectonophys., Kunming, China, 4, vol. 167, no. 4, pp. 81-91, pp. L13613, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Earthquake precursor: statistical anal. of seismicity ; Statistical investigations
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Seismotectonics and the earthquake frequency-magnitude distribution in the Aegean area (1989)
    In:  Geophys. J., San Francisco, Pergamon, vol. 98, no. B3, pp. 575-586, pp. 1447, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Earthquake ; Tectonics ; Seismicity ; Earthquake risk
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Central Washington seismicity: Evidence for a reactivated buried continental rift and northwest-trending structural zones (1989)
    In:  Geophys. Res. Lett., San Francisco, Schweizerbart'sche Verlagsbuchhandlung, vol. 16, no. 8, pp. 1325-1328, pp. B10404, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Geol. aspects ; Fault zone ; GRL
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Seismicity of the territory of Vietnam (1989)
    In:  Acta Geophys. Polonica, Basel, Elsevier Science Publishers, vol. XXXVII, no. 3, pp. 249-261, pp. L15S20, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; China ; FROTH, ; GMG-Bibl. ; BO
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Premonitory seismicity patterns near Vancouver Island, Canada (1989)
    In:  Tectonophys., Leipzig, 3-4, vol. 167, no. B6, pp. 299-312, pp. L15313, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Earthquake precursor: statistical anal. of seismicity ; Earthquake precursor: prediction research ; Subduction zone ; Pattern recognition
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    The 1960 Chilean Earthquakes (1989)
    In:  J. Geophys. Res., London, Institution of Mining and Metallurgy, vol. 94, no. 2, pp. 665-680, pp. 1869, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1989
    Keywords: Earthquake ; Seismicity ; Fault plane solution, focal mechanism ; Fore-shocks ; Aftershocks ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Active faulting and deformation of the Coalinga anticline as interpreted from three-dimensional velocity structure and seismicity (1989)
    In:  J. Geophys. Res., London, Amer. Sc., vol. 94, no. 4, pp. 15565-15586, pp. 1001, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1989
    Keywords: Geol. aspects ; Aftershocks ; Seismicity ; Fault zone ; Travel time ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Seismic strain rates in regions of distributed continental deformation (1989)
    In:  J. Geophys. Res., Münster, Amer. Sc., vol. 94, no. 4A, pp. 10231-10257, pp. L11609, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1989
    Keywords: Tectonics ; Seismicity ; Fault zone ; Moment tensor ; JGR ; Ekstroem ; Ekstrom
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Seismicity and tectonics of the Red Sea and western Arabia (1989)
    In:  Geophys. J., Münster, Amer. Sc., vol. 97, no. 11, pp. 449-457, pp. L11609, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Geol. aspects ; Tectonics ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Seismicity and tectonics of the Red Sea and western Arabia (1989)
    In:  Geophys. J. RAS, DGG and EGS, Münster, Amer. Sc., vol. 97, no. 11, pp. 449-457, pp. L11609, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Earthquake swarms precursory to moderate to great earthquakes in the northeast India region (1989)
    In:  Tectonophys., New York, Am. Soc. Mech. Eng., vol. 167, no. 14, pp. 285-298, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Earthquake precursor: statistical anal. of seismicity ; Fore-shocks ; Aftershocks
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Influence of fault plane heterogeneity on the seismic behavior in the southern Kurile Islands Arc (1989)
    In:  J. Geophys. Res., Luxembourg, Conseil de l'Europe, vol. 94, no. B10, pp. 5637-5649, pp. 1006, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Earthquake asperities ; Earthquake barriers ; Fault zone ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Seismotectonics at the Trench-Trench-Trench triple junction off central Honshu (1989)
    In:  Pure and Applied Geophysics, Luxembourg, Deutsche Geophys. Gesellschaft, vol. 129, no. 24, pp. 27-40, pp. 8045, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Geol. aspects ; Tectonics ; Plate tectonics ; Subduction zone ; Japan ; PAG
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    Brittle ductile transition, instability models of crustal rocks and the estimation of shallow source great earthquake depth (1989)
    In:  Geophys. J. R. astr. Soc., Taipei, AGU, vol. 66, no. 2, pp. 398-412, pp. L06307, 2 pp., (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: CRUST ; Tectonics ; Geol. aspects ; Plate tectonics ; Rheology ; Hypocentral depth ; Seismicity ; Rock mechanics ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 18
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    Long-term seismicity of North Armenia (1989)
    In:  Eos, Trans., Am. Geophys. Un., Luxembourg, EGS-Gauthier-Villars, vol. 70, no. 5, pp. 145, pp. 2214
    Details
    Publication Date: 1989
    Keywords: paleo ; Seismicity ; Earthquake precursor: prediction research
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    BIBLIOGRAPHY SEISMOLOGY
  • 19
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    Temporary seismic quiescence: SE Turkey (1989)
    In:  Geophys. J. RAS, DGG and EGS, Luxembourg, EGS-Gauthier-Villars, vol. 96, no. 5, pp. 311-331, pp. 2214
    Details
    Publication Date: 1989
    Keywords: Earthquake precursor: statistical anal. of seismicity ; paleo ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 20
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    Probabilistic assessment of earthquake hazard in Israel (1989)
    In:  Tectonophys., Amsterdam, Elsevier Scientific Publishing Company, vol. 167, no. B4, pp. 223-233, pp. B04401
    Details
    Publication Date: 1989
    Keywords: Earthquake hazard ; Statistical investigations ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 21
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    Great earthquakes and subduction along the Peru trench (1989)
    In:  Phys. Earth Plan. Int., Luxembourg, Conseil de l'Europe, vol. 57, no. 2, pp. 199-224, pp. 1892
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Subduction zone ; Fault zone ; South ; America ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 22
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    Some statistical aspects of earthquake occurrence in Iraq (1989)
    In:  Earthquake Spectra, Luxembourg, Am. Soc. Mech. Eng., vol. 5, no. 5, pp. 735-765, pp. 2099, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1989
    Keywords: Statistical investigations ; Seismicity ; Fault zone ; Earthquake hazard ; EQS
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    BIBLIOGRAPHY SEISMOLOGY
  • 23
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    Determination of fault planes at Coalinga, California, by analysis of patterns in aftershock locations (1989)
    In:  J. Geophys. Res., London, Am. Soc. Mech. Eng., vol. 94, no. B9, pp. 7496-7506, pp. B09401, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Fault zone ; Fault plane solution, focal mechanism ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 24
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    An evaluation of thermoluminescence dating of paleoearthquakes on the American Fork segment, Wasatch fault zone, Utah (1989)
    In:  J. Geophys. Res., Tokyo, Terra Scientific Publishing Company, vol. 94, no. 5, pp. 1622-1630, pp. B03312, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1989
    Keywords: Geol. aspects ; Seismicity ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 25
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    Earthquakes as a self-organized critical phenomenon (1989)
    In:  J. Geophys. Res., Washington D.C., Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 94, no. 1, pp. 15635-15637, pp. 2122
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Chaotic behaviour ; Energy (of earthquakes) ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 26
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    Microearthquake activity associated with underground coal-mining in Buchanan County, Virginia, USA (1989)
    In:  Pageoph, Warszawa, Elsevier, vol. 128, no. 1, pp. 407-421, pp. 2091, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Seismology ; Micro seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 27
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    Regional extent of the S wave reflector beneath the Kanto district, Japan (1989)
    In:  Geophys. Res. Lett., New York, California Division of Mines San Francisco, vol. 16, no. 31, pp. 639-842, pp. L03601, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Deep seismic sounding (espec. cont. crust) ; Subduction zone ; Seismicity ; GRL
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    BIBLIOGRAPHY SEISMOLOGY
  • 28
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    A more precise chronology of earthquakes produced by the San Andreas fault in southern California (1989)
    In:  J. Geophys. Res., Dordrecht, 89, vol. 94, no. 2, pp. 603-623, pp. TC5003, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Earthquake ; Geol. aspects ; Seismicity ; Earthquake precursor: prediction research ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 29
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    Microearthquake activity in the Dead Sea region (1989)
    In:  Geophys. J. Int., Luxembourg, Conseil de l'Europe, vol. 99, no. 5, pp. 605-620, pp. L05608, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; seismic Moment ; Corner frequency ; Fault plane solution, focal mechanism ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 30
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    Active tectonics of the Algerian Atlas Mountains- evidence from aftershocks of the 1980 El Asnam earthquake (1989)
    In:  Geophys. J. Int., Corvallis, x + 406 pp., Oregon State University Press, vol. 99, no. 8, pp. 761-788, pp. L13610, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Aftershocks ; Earthquake ; Tectonics ; Seismicity ; Fault zone ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 31
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    Earthquake Hazards and the Design of Constructed Facilities in the Eastern United States (1989)
    Academy of Sciences
    In:  New York, Academy of Sciences, vol. 558, no. XVI:, pp. 1-14, (ISBN 3-9808493-1-7)
    Details
    Publication Date: 1989
    Keywords: Seismology ; Seismicity ; Earthquake hazard
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    BIBLIOGRAPHY SEISMOLOGY
  • 32
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    Tectonic geomorphology and paleoseismology of the Septentrional fault system, Dominican Republic (1989)
    Geol. Soc. Am.
    In:  Bull., Polar Proj. OP-O3A4, Active Strike-slip and Collisional Tectonics of the Northern Caribbean Plate Boundary Zone, Washington, D. C., Geol. Soc. Am., vol. 326, no. 4, pp. 63-123, (ISBN 0080419208)
    Details
    Publication Date: 1989
    Keywords: Tectonics ; paleo ; Seismicity ; Fault zone ; Pena
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    BIBLIOGRAPHY SEISMOLOGY
  • 33
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    International Symposium on the Analysis of Seismicity and Seismic Hazard and Seismic Risk, 4.-9. Sept. 1989 (1989)
    Czechoslovak Academy of Sciences
    In:  Proceedings, 1., Prag, Czechoslovak Academy of Sciences, vol. 10, no. WS-693 7-83, pp. 235-239, (ISBN 3-933346-037)
    Details
    Publication Date: 1989
    Keywords: Seismology ; Seismicity ; Earthquake precursor: prediction research ; Earthquake risk ; Earthquake hazard ; Proceedings of a conference
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    BIBLIOGRAPHY SEISMOLOGY
  • 34
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    Precursory change of aftershock activity before large aftershock: A case study for recent earthquakes in China (1989)
    In:  J. Phys. Earth, Kunming, China, 3-4, vol. 37, no. 3, pp. 155-178, pp. B05301, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Earthquake precursor: prediction research ; Aftershocks ; Seismicity ; JPE
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    BIBLIOGRAPHY SEISMOLOGY
  • 35
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    Monitoring and Analysis of the Earthquake Swarm 1985/86 in the Region Vogtland/Western Bohemia (1989)
    Zentralinstitut für Physik der Erde
    In:  Potsdam, Zentralinstitut für Physik der Erde, vol. 70, pp. 158, (ISBN: 1-4020-0821-X)
    Details
    Publication Date: 1989
    Keywords: Earthquake ; Earthquake hazard ; Seismicity ; Project report/description
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    BIBLIOGRAPHY SEISMOLOGY
  • 36
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    The Earthquakes of Greece (1989)
    Ziti Publish. Co.
    In:  Thessaloniki, Ziti Publish. Co., vol. 15, no. Publ. No. 12, pp. 585, (ISBN 0080424309)
    Details
    Publication Date: 1989
    Keywords: Review article ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 37
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    On features of spatial and temporal variation of seismicity before and after moderate earthquakes (1989)
    In:  J. Phys. Earth, Washington, D.C., AGU, vol. 37, no. 9, pp. 179-200, pp. 1489, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Statistical investigations ; Earthquake precursor: prediction research ; JPE
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    BIBLIOGRAPHY SEISMOLOGY
  • 38
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    Mining-related and tectonic seismicity in the east mountain area Wasatch Plateau, Utah, USA (1989)
    In:  Pageoph, Hannover, Dt. Geophys. Ges. e. V., vol. 128, no. 51, pp. 344-368, pp. L15S14, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismology ; Tectonics ; Seismicity ; Rock bursts (see also ERDSTOSS and GEBIRGSSCHLAG)
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    BIBLIOGRAPHY SEISMOLOGY
  • 39
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    Observations of mine seismicity in the Eastern Wasatch Plateau, Utah, USA: A possible case of implosional failure (1989)
    In:  Pageoph, Köln, Elsevier, vol. 128, no. 16, pp. 369-405, pp. 1015, (ISSN: 1340-4202)
    Details
    Publication Date: 1989
    Keywords: Seismology ; Seismicity ; Source ; Rock bursts (see also ERDSTOSS and GEBIRGSSCHLAG)
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    BIBLIOGRAPHY SEISMOLOGY
  • 40
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    Catalogue of Focal Mechanisms of European Earthquakes (1989)
    Dept. of Geophysics, Universidad Complutense, Madrid, 274 pp.
    In:  Wokingham, Dept. of Geophysics, Universidad Complutense, Madrid, 274 pp., vol. 26, no. ALEX(01)-FR-77-01, AFTAC Contract F08606-76-C-0025, pp. 329, (ISBN: 0-08-043649-8)
    Details
    Publication Date: 1989
    Keywords: Earthquake catalog ; Fault plane solution, focal mechanism ; Seismicity ; Europe ; Middle ; East ; NAF ; Greece ; Turkey ; Aegean ; GFZ ; 15054, ; 000242798
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    BIBLIOGRAPHY SEISMOLOGY
  • 41
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    International Symposium on the Analysis of Seismicity and Seismic Hazard and Seismic Risk, 4.-9. Sept. 1989 (1989)
    Czechoslovak Academy of Sciences
    In:  Proceedings, 2., Prag, Czechoslovak Academy of Sciences, vol. 10, no. WS-693 7-83, pp. 235-239, (ISBN 3-933346-037)
    Details
    Publication Date: 1989
    Keywords: Seismology ; Seismicity ; Earthquake precursor: prediction research ; Earthquake risk ; Earthquake hazard ; Proceedings of a conference
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    BIBLIOGRAPHY SEISMOLOGY
  • 42
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    Multidisciplinary Research on Fault Activity in the western Part of the North Anatolian Fault Zone (2) (1989)
    Dep. of Appl. Phys., Tokyo Inst. of Technology, Tokyo, Japan and Dep. of Geophys., Kandilli Observ., Bogaziçi Univ., Istanbul, Turkey
    In:  report of, Hannover, Dep. of Appl. Phys., Tokyo Inst. of Technology, Tokyo, Japan and Dep. of Geophys., Kandilli Observ., Bogaziçi Univ., Istanbul, Turkey, vol. C 560, 183 pp., no. 23, pp. 595-596, (ISBN 3-933346-037)
    Details
    Publication Date: 1989
    Keywords: Earthquake precursor: prediction research ; Earthquake precursor: chemical (Rn, water(-level,...) ; Earthquake precursor: el. magn. ; Earthquake precursor: magnetic ; Geol. aspects ; Seismicity ; BIBTEX?
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    BIBLIOGRAPHY SEISMOLOGY
  • 43
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    A correlation between the b value and the fractal dimension of earthquakes (1989)
    In:  J. Geophys. Res., Hannover, Conseil de l'Europe, vol. 94, no. 8, pp. 7507-7514, pp. 1211, (ISSN 0343-5164)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; FractureT ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 44
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    Suche nach lokaler Seismizität mit dem kurzperiodischen Seismographennetz um die Georg-von-Neumayer-Station, Antarktis (1989)
    Alfred-Wegener-Institut
    In:  Diplomarbeit, Bremerhaven, Alfred-Wegener-Institut, vol. 10, no. No. 31, pp. 1431-1434, (ISBN 0 08 042822 3)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Seismology ; Antarctica ; Seismic networks ; Wuster
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    BIBLIOGRAPHY SEISMOLOGY
  • 45
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    Heat flow, electrical conductivity and seismicity in the Black Forest crust, SW Germany (1989)
    Am. Geophys. Union
    In:  Professional Paper, Open-File Rept., Properties and Processes of Earth's Lower Crust, San Diego, Am. Geophys. Union, vol. 22, no. 16, pp. 215-232, (ISBN 0080419208)
    Details
    Publication Date: 1989
    Keywords: Seismicity ; Geothermics ; Geoelectrics ; Muller
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    BIBLIOGRAPHY SEISMOLOGY
  • 46
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    Nonequilibrium hypersonic aerothermodynamics (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Nonequilibrium phenomena in hypersonic flows are examined on the basis of theoretical models and selected experimental data, in an introduction intended for second-year graduate students of aerospace engineering. Chapters are devoted to the physical nature of gas atoms and molecules, transitions of internal states, the formulation of the master equation of aerothermodynamics, the conservation equations, chemical reactions in CFD, the behavior of air flows in nonequilibrium, experimental aspects of nonequilibrium flow, a review of experimental results, and gas-solid interaction. Diagrams, graphs, and tables of numerical data are provided.
    Keywords: AERODYNAMICS
    Format: text
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  • 47
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    Transonic region of high dynamic response encountered on an elastic supercritical wing (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 870-875
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  • 48
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    Transonic aeroelasticity of fighter wings with active control surfaces (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 682-684
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  • 49
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    Hypersonic parabolized Navier-Stokes code validation on a sharp nose cone (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 650-656
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  • 50
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    Validation of aerodynamic parameters for high-incidence research models (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 621-628
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  • 51
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    Observation of airplane flowfields by natural condensation effects (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 593-604
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  • 52
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    Separation control on an airfoil by periodic forcing (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The introduction of transverse velocity fluctuations into a separated shear layer on an airfoil at high angles of attack is presently demonstrated to be an effective separation-control technique. Airfoil aerodynamic characteristics, including poststall lift and drag as well as maximum lift coefficient and stall angle, all exhibited improvements controlled forcing at 20 deg angle of attack led to an increased spreading of the mean velocity profile, together with increased turbulence activity; separation moved from the leading edge to about 80 percent of chord.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 27; 820
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  • 53
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    Boundary-layer transition on a cone and flat plate at Mach 3.5 (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 27; 687-693
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  • 54
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    Full-potential analysis of a supersonic delta wing/body (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 235-240
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  • 55
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    Direct simulation of three-dimensional hypersonic flow about intersecting blunt wedges (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 27; 1536-154
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  • 56
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    Turbulent separated flow over and downstream of a two-element airfoil (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Flow characteristics in the vicinity of the flap of a single-slotted airfoil are presented and analyzed. The flow remained attached over the model surfaces, except in the vicinity of the flap trailing edge where a small region of boundary-layer separation extended over the aft 7 percent of flap chord. The airfoil configuration was tested at a Mach number of 0.09 and a chord Reynolds number of 1.8 x 10 to the 6th in the NASA Ames Research Center 7- by 10-Foot Wind Tunnel. The flow was complicated by the presence of a strong, initially inviscid, jet, emanating from the slot between airfoil and flap, and a gradual merging of the main airfoil wake and flap suction-side boundary layer.
    Keywords: AERODYNAMICS
    Type: Experiments in Fluids (ISSN 0723-4864); 7; 8, Se
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  • 57
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    Aerothermodynamic study of slender conical vehicles (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 3; 361-367
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  • 58
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    Navier-Stokes computations of a prolate spheroid at angle of attack (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 986-993
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  • 59
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    Application of transonic flow analysis to helicopter rotor problems (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The transonic aspect of helicopter flow analysis is addressed. The equations of motion and their implementations are examined, and the computation of real rotor flows is considered. Nonlifting rotor flows, high-speed hover, high advance ratio lifting rotor flows, and strong blade/vortex interaction computations are discussed.
    Keywords: AERODYNAMICS
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  • 60
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    Basic numerical methods (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Some of the basic finite-difference schemes that can be used to solve the nonlinear equations that describe unsteady inviscid and viscous transonic flow are reviewed. Numerical schemes for solving the unsteady Euler and Navier-Stokes, boundary-layer, and nonlinear potential equations are described. Emphasis is given to the elementary ideas used in constructing various numerical procedures, not specific details of any one procedure.
    Keywords: AERODYNAMICS
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  • 61
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    Numerical study of chemically reacting flows using a lower-upper symmetric successive overrelaxation scheme (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 27; 1752-176
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  • 62
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    Navier-Stokes computations of lee-side flows over delta wings (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 27; 1673-167
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  • 63
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    Laminar-flow flight experiments (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The flight testing conducted over the past 10 years in the NASA laminar-flow control (LFC) will be reviewed. The LFC program was directed towards the most challenging technology application, the high supersonic speed transport. To place these recent experiences in perspective, earlier important flight tests will first be reviewed to recall the lessons learned at that time.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application and Experiment, Volume 2; p 59-104
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  • 64
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    Laminar-flow wind tunnel experiments (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Although most of the laminar flow airfoils recently developed at the NASA Langley Research Center were intended for general aviation applications, low-drag airfoils were designed for transonic speeds and wind tunnel performance tested. The objective was to extend the technology of laminar flow to higher Mach and Reynolds numbers and to swept leading edge wings representative of transport aircraft to achieve lower drag and significantly improved operation costs. This research involves stabilizing the laminar boundary layer through geometric shaping (Natural Laminar Flow, NLF) and active control involving the removal of a portion of the laminar boundary layer (Laminar-Flow Control, LFC), either through discrete slots or perforated surface. Results show that extensive regions of laminar flow with large reductions in skin friction drag can be maintained through the application of passive NLF boundary-layer control technologies to unswept transonic wings. At even greater extent of laminar flow and reduction in the total drag level can be obtained on a swept supercritical airfoil with active boundary layer-control.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application and Experiment, Volume 2; p 105-145
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  • 65
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    Reynolds number effects on the transonic aerodynamics of a slender wing-body configuration (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Aerodynamic forces and moments for a slender wing-body configuration are summarized from an investigation in the Langley National Transonic Facility (NTF). The results include both longitudinal and lateral-directional aerodynamic properties as well as slideslip derivatives. Results were selected to emphasize Reynolds number effects at a transonic speed although some lower speed results are also presented for context. The data indicate nominal Reynolds number effects on the longitudinal aerodynamic coefficients and more pronounced effects for the lateral-directional aerodynamic coefficients. The Reynolds number sensitivities for the lateral-directional coefficients were limited to high angles of attack.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application and Experiment, Volume 2; p 41-58
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  • 66
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    A review of high-speed, convective, heat-transfer computation methods (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The objective is to provide useful engineering formulations and to instill a modest degree of physical understanding of the phenomena governing convective aerodynamic heating at high flight speeds. Some physical insight is not only essential to the application of the information presented here, but also to the effective use of computer codes which may be available to the reader. Given first is a discussion of cold-wall, laminar boundary layer heating. A brief presentation of the complex boundary layer transition phenomenon follows. Next, cold-wall turbulent boundary layer heating is discussed. This topic is followed by a brief coverage of separated flow-region and shock-interaction heating. A review of heat protection methods follows, including the influence of mass addition on laminar and turbulent boundary layers. Next is a discussion of finite-difference computer codes and a comparison of some results from these codes. An extensive list of references is also provided from sources such as the various AIAA journals and NASA reports which are available in the open literature.
    Keywords: AERODYNAMICS
    Type: Nielsen Engineering and Research, Inc., Missile Aerodynamics: NEAR Conference on Missile Aerodynamics; 64 p
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  • 67
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    Experience with some repeat tests on the 9 inch chord CAST-10-2/DOA 2 airfoil model in the Langley 0.3-m TCT adaptive wall test section (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: A co-operative testing program is in progress between the Langley Research Center (NASA) and the National Aeronautical Establishment (NAE, Canada) to validate two different techniques of airfoil testing at transonic speeds. The procedure employed is to test the same airfoil model in the NAE two-dimensional tunnel and the Langley 0.3-m Transonic Cryogenic Tunnel (0.3-m TCT). The airfoil model used in testing was CAST-10-2/DOA-2 super-critical airfoil. The Langley 0.3-m TCT has a relatively small cross section of 13 in x 13 in, giving a (h/c) ratio of 1.44 for the same 9 in chord model. The approach employed in the 0.3-m TCT aims towards eliminating the wall effects by using active walls. The top and bottom walls are flexible. By changing the wall shapes during a test in an iterative manner, the wall interference effects are reduced. The method employed to change the wall shapes is the adaptive wall technique. The current test program provided an opportunity to validate the adaptive wall technique in the 0.3-m TCT. The relatively long chord airfoil represents a severe test case to test the efficacy of the adaptive wall technique under cryogenic conditions. The program also involved removal of side wall boundary-layer thus increasing the complexity of the wall adaptation technique. This paper deals with some salient results obtained regarding repeatability of test data and possible residual interference effects.
    Keywords: AERODYNAMICS
    Type: CAST-10-2(DOA 2 Airfoil Studies Workshop Results; p 213-231
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    Comparison of two- and three-dimensional Navier-Stokes solutions with NASA experimental data for CAST-10 airfoil (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The two-dimensional (2-D) and three-dimensional Navier-Stokes equations are solved for flow over a NAE CAST-10 airfoil model. Recently developed finite-volume codes that apply a multistage time stepping scheme in conjunction with steady state acceleration techniques are used to solve the equations. Two-dimensional results are shown for flow conditions uncorrected and corrected for wind tunnel wall interference effects. Predicted surface pressures from 3-D simulations are compared with those from 2-D calculations. The focus of the 3-D computations is the influence of the sidewall boundary layers. Topological features of the 3-D flow fields are indicated. Lift and drag results are compared with experimental measurements.
    Keywords: AERODYNAMICS
    Type: CAST-10-2(DOA 2 Airfoil Studies Workshop Results; p 233-258
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  • 69
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    An experimental AWTS process and comparisons of ONERA T2 and 0.3-m TCT AWTS data for the ONERA CAST-10 aerofoil (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: An experimental Adaptive Wall Test Section (AWTS) process is described. Comparisons of the ONERA T2 and the 0.3-m TCT (transonic cryogenic tunnel) AWTS data for the ONERA CAST-10 airfoil are presented. Most of the 0.3-m TCT data is new and preliminary and no sidewall boundary layer control is involved. No conclusions are given.
    Keywords: AERODYNAMICS
    Type: CAST-10-2(DOA 2 Airfoil Studies Workshop Results; p 137-153
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  • 70
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    High Reynolds number tests of the CAST-10-2/DOA 2 transonic airfoil at ambient and cryogenic temper ature conditions (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The transonic airfoil CAST 10-2/DOA 2 was investigated in several major transonic wind tunnels at Reynolds numbers ranging from Re=1.3 x 10(exp 6) to 45 x 10(exp 6) at ambient and cryogenic temperature conditions. The main objective was to study the degree and extent of the effects of Reynolds number on both the airfoil aerodynamic characteristics and the interference effects of various model-wind-tunnel systems. The initial analysis of the CAST 10-2 airfoil results revealed appreciable real Reynolds number effects on this airfoil and showed that wall interference can be significantly affected by changes in Reynolds number thus appearing as true Reynolds number effects.
    Keywords: AERODYNAMICS
    Type: CAST-10-2(DOA 2 Airfoil Studies Workshop Results; p 47-60
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  • 71
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    Finite element flow-thermal-structural analysis of aerodynamically heated leading edges (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Hypersonic vehicles operate in a hostile aerothermal environment which has a significant impact on their aerothermostructural performance. Significant coupling occurs between the aerodynamic flow field, structural heat transfer, and structural response creating a multidisciplinary interaction. A long term goal of the Aerothermal Loads Branch at the NASA Langley Research Center is to develop a computational capability for integrated fluid, thermal and structural analysis of aerodynamically heated structures. The integrated analysis capability includes the coupling between the fluid and the structure which occurs primarily through the thermal response of the structure, because: (1) the surface temperature affects the external flow by changing the amount of energy absorbed by the structure, and (2) the temperature gradients in the structure result in structural deformations which alter the flow field and attendant surface pressures and heating rates. In the integrated analysis, a finite element method is used to solve: (1) the Navier-Stokes equations for the flow solution, (2) the energy equation of the structure for the temperature response, and (3) the equilibrium equations of the structure for the structural deformation and stresses.
    Keywords: AERODYNAMICS
    Type: Recent Advances in Multidisciplinary Analysis and Optimization, Part 2; p 971-990
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  • 72
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    Wall interference assessment and corrections (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Wind tunnel wall interference assessment and correction (WIAC) concepts, applications, and typical results are discussed in terms of several nonlinear transonic codes and one panel method code developed for and being implemented at NASA-Langley. Contrasts between 2-D and 3-D transonic testing factors which affect WIAC procedures are illustrated using airfoil data from the 0.3 m Transonic Cryogenic Tunnel and Pathfinder 1 data from the National Transonic Facility. Initial results from the 3-D WIAC codes are encouraging; research on and implementation of WIAC concepts continue.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 817-851
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  • 73
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    Stability of compressible boundary layers (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The stability of compressible 2-D and 3-D boundary layers is reviewed. The stability of 2-D compressible flows differs from that of incompressible flows in two important features: There is more than one mode of instability contributing to the growth of disturbances in supersonic laminar boundary layers and the most unstable first mode wave is 3-D. Whereas viscosity has a destabilizing effect on incompressible flows, it is stabilizing for high supersonic Mach numbers. Whereas cooling stabilizes first mode waves, it destabilizes second mode waves. However, second order waves can be stabilized by suction and favorable pressure gradients. The influence of the nonparallelism on the spatial growth rate of disturbances is evaluated. The growth rate depends on the flow variable as well as the distance from the body. Floquet theory is used to investigate the subharmonic secondary instability.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 629-689
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  • 74
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    Turbulent eddy viscosity modeling in transonic shock/boundary-layer interactions (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The treatment of turbulence effects on transonic shock/turbulent boundary layer interaction is addressed within the context of a triple deck approach valid for arbitrary practical Reynolds numbers between 1000 and 10 billion. The modeling of the eddy viscosity and basic turbulent boundary profile effects in each deck is examined in detail using Law-of-the-Wall/Law-of-the-Wake concepts as the foundation. Results of parametric studies showing how each of these turbulence model aspects influences typical interaction zone property distributions (wall pressure, displacement thickness and local skin friction) are presented and discussed.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 611-627
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  • 75
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    Airframe/propulsion integration characteristics at transonic speeds (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The aerodynamic characteristics for both single and twin-engine high-performance aircraft are significantly affected by shock induced flow interactions as well as other local flow interference effects which usually occur at transonic speeds. These adverse interactions can not only cause high drag, but also cause unusual aerodynamic loadings and/or severe stability and control problems. Many programs are under way to not only develop method for reducing the adverse effects, but also to develop an understanding of the basic flow conditions which are the primary contributors. It is anticipated that these programs will result in technologies which can reduce the aircraft cruise drag through improved integration as well as increase aircraft maneuverability through the application of thrust vectoring. Some of the primary integration problems for twin-engine aircraft at transonic speeds are identified, and several methods are demonstrated for reducing or eliminating the undersirable characteristics, while enhancing configuration effectiveness.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 1-31
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    Generation of unstructured grids and Euler solutions for complex geometries (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Algorithms are described for the generation and adaptation of unstructured grids in two and three dimensions, as well as Euler solvers for unstructured grids. The main purpose is to demonstrate how unstructured grids may be employed advantageously for the economic simulation of both geometrically as well as physically complex flow fields.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 377-408
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  • 77
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    Asymptotic methods for internal transonic flows (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: For many internal transonic flows of practical interest, some of the relevant nondimensional parameters typically are small enough that a perturbation scheme can be expected to give a useful level of numerical accuracy. A variety of steady and unsteady transonic channel and cascade flows is studied with the help of systematic perturbation methods which take advantage of this fact. Asymptotic representations are constructed for small changes in channel cross-section area, small flow deflection angles, small differences between the flow velocity and the sound speed, small amplitudes of imposed oscillations, and small reduced frequencies. Inside a channel the flow is nearly one-dimensional except in thin regions immediately downstream of a shock wave, at the channel entrance and exit, and near the channel throat. A study of two-dimensional cascade flow is extended to include a description of three-dimensional compressor-rotor flow which leads to analytical results except in thin edge regions which require numerical solution. For unsteady flow the qualitative nature of the shock-wave motion in a channel depends strongly on the orders of magnitude of the frequency and amplitude of impressed wall oscillations or fluctuations in back pressure. One example of supersonic flow is considered, for a channel with length large compared to its width, including the effect of separation bubbles and the possibility of self-sustained oscillations. The effect of viscosity on a weak shock wave in a channel is discussed.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 261-291
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  • 78
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    Euler solvers for transonic applications (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The 1980s may well be called the Euler era of applied aerodynamics. Computer codes based on discrete approximations of the Euler equations are now routinely used to obtain solutions of transonic flow problems in which the effects of entropy and vorticity production are significant. Such codes can even predict separation from a sharp edge, owing to the inclusion of artificial dissipation, intended to lend numerical stability to the calculation but at the same time enforcing the Kutta condition. One effect not correctly predictable by Euler codes is the separation from a smooth surface, and neither is viscous drag; for these some form of the Navier-Stokes equation is needed. It, therefore, comes as no surprise to observe that the Navier-Stokes has already begun before Euler solutions were fully exploited. Moreover, most numerical developments for the Euler equations are now constrained by the requirement that the techniques introduced, notably artificial dissipation, must not interfere with the new physics added when going from an Euler to a full Navier-Stokes approximation. In order to appreciate the contributions of Euler solvers to the understanding of transonic aerodynamics, it is useful to review the components of these computational tools. Space discretization, time- or pseudo-time marching and boundary procedures, the essential constituents are discussed. The subject of grid generation and grid adaptation to the solution are touched upon only where relevant. A list of unanswered questions and an outlook for the future are covered.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 217-230
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    Transonics and fighter aircraft: Challenges and opportunities for CFD (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The application of computational fluid dynamics (CFD) to fighter aircraft design and development is discussed. Methodology requirements for the aerodynamic design of fighter aircraft are briefly reviewed. The state-of-the-art of computational methods for transonic flows in the light of these requirements is assessed and the techniques found most adequate for the subject application are identified. Highlights from some proof-of-feasibility Euler and Navier-Stokes computations about a complete fighter aircraft configuration are presented. Finally, critical issues and opportunities for design application of CFD are discussed.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 153-173
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  • 80
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    Shock-boundary-layer interaction in flight (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: A brief survey is given on the study of transonic shock/boundary layer effects in flight. Then the possibility of alleviating the adverse shock effects through passive shock control is discussed. A Swedish flight experiment on a swept wing attack aircraft is used to demonstrate how it is possible to reduce the extent of separated flow and increase the drag-rise Mach number significantly using a moderate amount of perforation of the surface.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 61-77
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    Two-measured variable method for wall interference assessment/correction (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An iterative method for wall interference assessment and/or correction is presented for transonic flow conditions in wind tunnels equipped with two component velocity measurements on a single interface. The iterative method does not require modeling of the test article and tunnel wall boundary conditions. Analytical proof for the convergence and stability of the iterative method is shown in the subsonic flow regime. The numerical solutions are given for both 2-D and axisymmetrical cases at transonic speeds with the application of global Mach number correction.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 853-866
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  • 82
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    Developments and trends in three-dimensional mesh generation (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: An intense research effort over the last few years has produced several competing and apparently diverse methods for generating meshes. Recent progress is reviewed and the central themes are emphasized which form a solid foundation for future developments in mesh generation.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 341-376
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  • 83
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    An embedded mesh procedure for leading-edge vortex flows (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: A cell-vertex scheme is outlined for solving the flow about a delta wing with M (sub infinity) is greater than 1. Embedded regions of mesh refinement allow solutions to be obtained which have much higher resolution than those achieved to date. Effects of mesh refinement and artificial viscosity on the solutions are studied, to determine at what point leading-edge vortex solutions are grid-converged. A macroscale and a microscale for the size of the vortex are defined, and it is shown that the macroscale (which includes the wing surface properties) is converged on a moderately refined grid, while the microscale is very sensitive to grid spacing. The level of numerical diffusion in the core of the vortex is found to be substantial. Comparisons with the experiment are made for two cases which have transonic cross-flow velocities.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 231-259
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  • 84
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    Computation of aircraft component flow fields at transonic Mach numbers using a three-dimensional Navier-Stokes algorithm (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A computer analysis was developed for calculating steady (or unsteady) three-dimensional aircraft component flow fields. This algorithm, called ENS3D, can compute the flow field for the following configurations: diffuser duct/thrust nozzle, isolated wing, isolated fuselage, wing/fuselage with or without integrated inlet and exhaust, nacelle/inlet, nacelle (fuselage) afterbody/exhaust jet, complete transport engine installation, and multicomponent configurations using zonal grid generation technique. Solutions can be obtained for subsonic, transonic, or hypersonic freestream speeds. The algorithm can solve either the Euler equations for inviscid flow, the thin shear layer Navier-Stokes equations for viscous flow, or the full Navier-Stokes equations for viscous flow. The flow field solution is determined on a body-fitted computational grid. A fully-implicit alternating direction implicit method is employed for the solution of the finite difference equations. For viscous computations, either a two layer eddy-viscosity turbulence model or the k-epsilon two equation transport model can be used to achieve mathematical closure.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 175-194
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  • 85
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    Transonic CFD applications at Boeing (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The use of computational methods for three dimensional transonic flow design and analysis at the Boeing Company is presented. A range of computational tools consisting of production tools for every day use by project engineers, expert user tools for special applications by computational researchers, and an emerging tool which may see considerable use in the near future are described. These methods include full potential and Euler solvers, some coupled to three dimensional boundary layer analysis methods, for transonic flow analysis about nacelle, wing-body, wing-body-strut-nacelle, and complete aircraft configurations. As the examples presented show, such a toolbox of codes is necessary for the variety of applications typical of an industrial environment. Such a toolbox of codes makes possible aerodynamic advances not previously achievable in a timely manner, if at all.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 79-107
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  • 86
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    Transition to turbulence in laminar hypersonic flow (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Progress in a recently started project aimed at the prediction of transition to turbulence in hypersonic flow is briefly discussed. The prediction of transition to turbulence is a very important issue in the design of space vessels. Two space vehicles currently under investigation, namely the aeroassisted transfer vehicle (AOTV) and the trans-atmospheric vehicle (TAV), suffer from strong aerodynamic heating. This heating is strongly influenced by the boundary layer structure. These aerospace vehicles fly in the upper atmospheric layer at a Mach number between 10 and 30 at very low atmospheric pressures. At very high altitudes the flow is laminar, but when the space vessel returns to a lower orbit, the flow becomes turbulent and the heating is dramatically increased. The prediction of this transition process is commonly done by means of experiments. The experimental facilities available nowadays cannot model the hypersonic flow field accurately enough by limitations in Mach and Reynolds number. These facilities also have a large free stream disturbance level which makes it very difficult to investigate transition accurately. An alternative approach is to study transition by theoretical means. Up to now numerical studies of hypersonic flow only discussed steady laminar or turbulent flow. This theoretical approach is extended to the study of transition in hypersonic flow by means of direct numerical simulations and additional theoretical investigations to explain the mechanisms leading to transition. A brief outline of how this research is to be performed is given.
    Keywords: AERODYNAMICS
    Type: Annual Research Briefs, 1988; p 115-119
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  • 87
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    Computational aeroelasticity challenges and resources (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: In the past decade, there has been much activity in the development of computational methods for the analysis of unsteady transonic aerodynamics about airfoils and wings. Significant features are illustrated which must be addressed in the treatment of computational transonic unsteady aerodynamics. The flow regimes for an aircraft on a plot of lift coefficient vs. Mach number are indicated. The sequence of events occurring in air combat maneuvers are illustrated. And further features of transonic flutter are illustrated. Also illustrated are several types of aeroelastic response which were encountered and which offer challenges for computational methods. The four cases illustrate problem areas encountered near the boundaries of aircraft envelopes, as operating condition change from high speed, low angle conditions to lower speed, higher angle conditions.
    Keywords: AERODYNAMICS
    Type: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 2; p 631-637
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  • 88
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    Full potential unsteady computations including aeroelastic effects (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A unified formulation is presented based on the full potential framework coupled with an appropriate structural model to compute steady and unsteady flows over rigid and flexible configurations across the Mach number range. The unsteady form of the full potential equation in conservation form is solved using an implicit scheme maintaining time accuracy through internal Newton iterations. A flux biasing procedure based on the unsteady sonic reference conditions is implemented to compute hyperbolic regions with moving sonic and shock surfaces. The wake behind a trailing edge is modeled using a mathematical cut across which the pressure is satisfied to be continuous by solving an appropriate vorticity convection equation. An aeroelastic model based on the generalized modal deflection approach interacts with the nonlinear aerodynamics and includes both static as well as dynamic structural analyses capability. Results are presented for rigid and flexible configurations at different Mach numbers ranging from subsonic to supersonic conditions. The dynamic response of a flexible wing below and above its flutter point is demonstrated.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 1; p 175-191
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  • 89
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    Application of a full potential method to AGARD standard airfoils (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: One of the most important uses of method that calculate unsteady aerodynamic loads is to predict and analyze the aeroelastic responses of flight vehicles. Currently, methods based on transonic small disturbance potential aerodynamics are the primary tools for aeroelastic analysis. Flow solutions obtained using isentropic potential theory can be highly inaccurate and even multivalued, because they do not model the effects of entropy that is produced when shock waves are in the flow field. From the results that are presented, it is concluded that nonisentropic potential methods more accurately model Euler solutions than do isentropic methods. The primary effects of modeling shock generated entropy are: (1) to eliminate mulitple flow solutions when strong shock waves are in the flow field; and (2) to bring the strengths and locations of computed shock waves into better agreement with those calculated using Euler method and those measured during experiments.
    Keywords: AERODYNAMICS
    Type: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 1; p 157-174
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  • 90
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    Calculation of steady and unsteady pressures at supersonic speeds with CAP-TSD (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A finite difference technique is used to solve the transonic small disturbance flow equation making use of shock capturing to treat wave discontinuities. Thus the nonlinear effects of thickness and angle of attack are considered. Such an approach is made feasible by the development of a new code called CAP-TSD (Computational Aeroelasticity Program - Transonic Small Disturbance), and is based on a fully implicit approximate factorization (AF) finite difference method to solve the time dependent transonic small disturbance equation. The application of the CAP-TSD code to the calculation of low to moderate supersonic steady and unsteady flows is presented. In particular, comparisons with exact linear theory solutions are made for steady and unsteady cases to evaluate shock capturing and other features of the current method. In addition, steady solutions obtained from an Euler code are used to evaluate the small disturbance aspects of the code. Steady and unsteady pressure comparisons are made with measurements for an F-15 wing model and for the RAE tailplane model.
    Keywords: AERODYNAMICS
    Type: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 1; p 117-137
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  • 91
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    Comparison of airfoil results from an adaptive wall test section and a porous wall test section (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Two wind tunnel investigations were conducted to assess two different wall interference alleviation/correction techniques: adaptive test section walls and classical analytical corrections. The same airfoil model has been tested in the adaptive wall test section of the NASA-Langley 0.3 m Transonic Cryogenic Tunnel (TCT) and in the National Aeronautical Establishment (NAE) High Reynolds Number 2-D facility. The model has a 9 in. chord and a CAST 10-2/DOA 2 airfoil section. The 0.3 m TCT adaptive wall test section has four solid walls with flexible top and bottom walls. The NAE test section has porous top and bottom walls and solid side walls. The aerodynamic results corrected for top and bottom wall interference at Mach numbers from 0.3 to 0.8 at a Reynolds number of 10 by 1,000,000. Movement of the adaptive walls was used to alleviate the top and bottom wall interference in the test results from the NASA tunnel.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 867-890
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  • 92
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    An LDA (Laser-Doppler Anemometry) investigation of three-dimensional normal shock wave boundary-layer interactions (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Nonintrusive measurements were made of a normal shock wave/boundary layer interaction. Two dimensional measurements were made throughout the interaction region while 3-D measurements were made in the vicinity of the shock wave. The measurements were made in the corner of the test section of a continuous supersonic wind tunnel in which a normal shock wave had been stabilized. Laser Doppler Anemometry, surface pressure measurement and flow visualization techniques were employed for two freestream Mach number test cases: 1.6 and 1.3. The former contained separated flow regions and a system of shock waves. The latter was found to be far less complicated. The results define the flow field structure in detail for each case.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 741-764
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  • 93
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    Secondary three-dimensional instability in compressible boundary layers (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Three dimensional linear secondary instability theory is extended for compressible boundary layers on a flat plate in the presence of finite amplitude Tollmien-Schlichting waves. The focus is on principal parametric resonance responsible for strong growth of subharmonics in low disturbance environment.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 691-704
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  • 94
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    Turbulence and modeling in transonic flow (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: A review is made of the performance of a variety of turbulence models in the evaluation of a particular well documented transonic flow. This is done to supplement a previous attempt to calibrate and verify transonic airfoil codes by including many more turbulence models than used in the earlier work and applying the calculations to an experiment that did not suffer from uncertainties in angle of attack and was free of wind tunnel interference. It is found from this work, as well as in the earlier study, that the Johnson-King turbulence model is superior for transonic flows over simple aerodynamic surfaces, including moderate separation. It is also shown that some field equation models with wall function boundary conditions can be competitive with it.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 581-610
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  • 95
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    Euler/Navier-Stokes calculations of transonic flow past fixed- and rotary-wing aircraft configurations (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Computational fluid dynamics has an increasingly important role in the design and analysis of aircraft as computer hardware becomes faster and algorithms become more efficient. Progress is being made in two directions: more complex and realistic configurations are being treated and algorithms based on higher approximations to the complete Navier-Stokes equations are being developed. The literature indicates that linear panel methods can model detailed, realistic aircraft geometries in flow regimes where this approximation is valid. As algorithms including higher approximations to the Navier-Stokes equations are developed, computer resource requirements increase rapidly. Generation of suitable grids become more difficult and the number of grid points required to resolve flow features of interest increases. Recently, the development of large vector computers has enabled researchers to attempt more complex geometries with Euler and Navier-Stokes algorithms. The results of calculations for transonic flow about a typical transport and fighter wing-body configuration using thin layer Navier-Stokes equations are described along with flow about helicopter rotor blades using both Euler/Navier-Stokes equations.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 521-545
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  • 96
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    Aerodynamic analysis of three advanced configurations using the TranAir full-potential code (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Computational results are presented for three advanced configurations: the F-16A with wing tip missiles and under wing fuel tanks, the Oblique Wing Research Aircraft, and an Advanced Turboprop research model. These results were generated by the latest version of the TranAir full potential code, which solves for transonic flow over complex configurations. TranAir embeds a surface paneled geometry definition in a uniform rectangular flow field grid, thus avoiding the use of surface conforming grids, and decoupling the grid generation process from the definition of the configuration. The new version of the code locally refines the uniform grid near the surface of the geometry, based on local panel size and/or user input. This method distributes the flow field grid points much more efficiently than the previous version of the code, which solved for a grid that was uniform everywhere in the flow field. TranAir results are presented for the three configurations and are compared with wind tunnel data.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 437-452
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  • 97
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    Vector potential methods (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Vector potential and related methods, for the simulation of both inviscid and viscous flows over aerodynamic configurations, are briefly reviewed. The advantages and disadvantages of several formulations are discussed and alternate strategies are recommended. Scalar potential, modified potential, alternate formulations of Euler equations, least-squares formulation, variational principles, iterative techniques and related methods, and viscous flow simulation are discussed.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 309-339
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  • 98
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    Transonic aerodynamic design experience (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Advancements have occurred in transonic numerical simulation that place aerodynamic performance design into a relatively well developed status. Efficient broad band operating characteristics can be reliably developed at the conceptual design level. Recent aeroelastic and separated flow simulation results indicate that systematic consideration of an increased range of design problems appears promising. This emerging capability addresses static and dynamic structural/aerodynamic coupling and nonlinearities associated with viscous dominated flows.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 195-216
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  • 99
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    Applied transonics at Grumman (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: A review of several applications of Computational Fluid Dynamics (CFD) to various aspects of aerodynamic design recently carried out at Grumman is presented. The emphasis is placed on project-oriented applications where the ease of use of the methods and short start-to-completion times are required. Applications cover transonic wing design/optimization, wing mounted stores load prediction, transonic buffet alleviation, fuselage loads estimation, and compact offset diffuser design for advanced aircraft configurations. Computational methods employed include extended transonic small disturbance (automatic grid embedding) formulation for analysis/design/optimization and a thin layer Navier-Stokes formulation for both external and internal flow analyses.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 133-152
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  • 100
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    The application of CFD for military aircraft design at transonic speeds (1989)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Numerous computational fluid dynamics (CFD) codes are available that solve any of several variations of the transonic flow equations from small disturbance to full Navier-Stokes. The design philosophy at General Dynamics Fort Worth Division involves use of all these levels of codes, depending on the stage of configuration development. Throughout this process, drag calculation is a central issue. An overview is provided for several transonic codes and representative test-to-theory comparisons for fighter-type configurations are presented. Correlations are shown for lift, drag, pitching moment, and pressure distributions. The future of applied CFD is also discussed, including the important task of code validation. With the progress being made in code development and the continued evolution in computer hardware, the routine application of these codes for increasingly more complex geometries and flow conditions seems apparent.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 109-132
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