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  • AERODYNAMICS  (420)
  • Seismicity
  • 1980-1984  (452)
  • 1935-1939  (5)
  • 1982  (452)
  • 1939  (5)
  • 1
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    Tsunamis and earthquakes (1939)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 29, no. 6, pp. 517-526, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Der Hohenzollerngraben und Intraplattenseismizität infolge Verwitterung lamellärer Scherung mit einer Riftstruktur (1982)
    In:  Oberrhein. geol. Abh., Karlsruhe, Schweizerbart'sche Verlagsbuchhandlung, vol. 31, no. 11/12, pp. 47-78, pp. L08309, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1982
    Keywords: Stress ; Fault zone ; Seismicity ; rifting ; Geol. aspects ; Tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Seismicity, normal faulting, and geomorphological development of the gulf of Corinth (Greece): The Corinth earthquake of February and March 1981 (1982)
    In:  Earth Planet. Sci. Lett., Amsterdam, Schweizerbart'sche Verlagsbuchhandlung, vol. 57, no. 2, pp. 377-397, pp. L07302, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Dip-slip ; Earthquake ; Geol. aspects ; EPSL
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Earthquake swarms as a long-range precursor to large earthquakes in Turkey (1982)
    In:  Geophys. J. R. astr. Soc., Kalamazoo, Michigan 49001, The Upjohn Company, vol. 68, no. B8, pp. 459-476, pp. L09603, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Earthquake precursor: statistical anal. of seismicity ; Toksoez ; Toksoz ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Variations in seismicity as a fundamental tool in earthquake prediction (1982)
    In:  Bull. Seism. Soc. Am., New York, August, vol. 72 spec. symp. iss., no. 3, pp. S351-S366, pp. B05S05, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Earthquake precursor: prediction research ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    A microearthquake survey of Bouvet Island, South Atlantic (1982)
    In:  Tectonophys., Warszawa, Applied Science Publishers LTD, vol. 81, no. 1, pp. 1-5, pp. L07307, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Volcanology ; Seismic networks
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Some aspects of viscous stress relaxation and intraplate seismicity (1982)
    In:  Tectonophys., Basel, Elsevier Science Publishers, vol. 82, no. B3, pp. T1-T9, pp. B03304, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Inelastic ; Plate tectonics ; Stress ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Limits of stresses in continental crusts and their relation to the depth-frequency distribution of shallow earthquakes (1982)
    In:  Tectonics, Hannover, Conseil de l'Europe, vol. 1, no. 1-2, pp. 73-89, pp. L19605, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: CRUST ; Tectonics ; Stress ; Seismicity ; Rheology ; Hypocentral depth
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Seismic Energy mapping applied to Turkey (1982)
    In:  Tectonophys., Ottawa, Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 82, no. 3-4, pp. 69-87, pp. L14310
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Energy (of earthquakes) ; Waves ; Dynamic ; FROTH ; (abstract)
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    An ancient rift complex and its relation to contemporary seismicity in the New Madrid seismic zone (1982)
    In:  Tectonics, Leipzig, 3-4, vol. 1, no. 6, pp. 225-237, pp. L19606, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; USA ; intra-continental ; Tectonics ; basin
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Seismotectonics of the southern boundary of Anatolia, eastern Mediterranean region: Subduction, collision, and arc jumping (1982)
    In:  J. Geophys. Res., Kobe, Dec. 6-11, 1993, The Local Organizing Committee for the CRCM '93, vol. 87, no. 2, pp. 7694-7706, pp. 1893, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Turkey ; Tectonics ; Seismicity ; Subduction zone ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Magmatic resurgence in Long Valley caldera, California: Possible cause of the 1980 Mammoth Lakes earthquakes (1982)
    In:  Science, Hokkaido University, Inst. f. Geophys., Ruhr-Univ. Bochum, vol. 217, no. B2, pp. 531-533, pp. B02403, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Volcanology ; Seismology ; Seismicity ; Stress
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Subduction seismicity and tectonics in the Lesser Antilles arc (1982)
    In:  J. Geophys. Res., Houston, Pergamon, vol. 87, no. 5688, pp. 8642-8664, pp. B05S01, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Subduction zone ; Seismicity ; Plate tectonics ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Central Mississippi Valley Earthquake Bulletin (1982)
    Saint Louis University
    In:  Garland, Saint Louis University, vol. 1, no. Publ. No. 12, pp. 95-104, (ISBN: 0-08-043930-6)
    Details
    Publication Date: 1982
    Keywords: Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Source Properties of the Oates Land earthquake, October 1974 (1982)
    In:  Antarctic Geoscience, London, Geological Society, London & Blackwell Scientific Publications, vol. 65, pp. 955-958
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    Publication Date: 1982
    Keywords: Earthquake ; Seismicity ; ENDNOTE?
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Comparison between the North Anatolian fault of Turkey and the San Andreas fault of California (1982)
    Vieweg
    In:  Multidisciplinary Approach to Earthquake Prediction, Braunschweig, Vieweg, vol. 462, pp. 67-85
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Earthquake precursor: prediction research ; Fault zone ; NAF ; Tectonics ; Plate tectonics ; Earthquake hazard ; Creep observations and analysis ; Isikara
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    A comparison between the tectonic stress measured fIin situfR and stress parameters for induced seismicity at Monticello Reservoir, South Carolina (1982)
    In:  J. Geophys. Res., Tokyo, Terra Scientific Publishing Company, vol. 87, no. B3, pp. 6931-6944, pp. B03312, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1982
    Keywords: Tectonics ; Stress ; Seismicity ; Source parameters ; Fault plane solution, focal mechanism ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 18
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    Migration of regional seismicity, before some great earthquakes (1982)
    In:  Acta Geophysica Sinica, Klagenfurt, Nuclear Technology Publ., vol. 25, no. 3, pp. 509-515, pp. L21601, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1982
    Keywords: Seismicity ; China ; seismic Migration
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    BIBLIOGRAPHY SEISMOLOGY
  • 19
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    Duration of the sequence of strong aftershocks of a major earthquake (1982)
    In:  Acta Seismologica Sinica, Klagenfurt, Nuclear Technology Publ., vol. 4, no. 3, pp. 389-394, pp. L21601, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1982
    Keywords: Seismicity ; Aftershocks ; China
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    BIBLIOGRAPHY SEISMOLOGY
  • 20
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    The structure of the Pacific basin as indicated by earthquakes (1939)
    In:  Science, Milano, Gustav Fischer, vol. 90, no. 6, pp. 456-458, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 21
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    Depth and geographical distribution of deep-focus earthquakes II (1939)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 50, no. 6, pp. 1511-1528, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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    BIBLIOGRAPHY SEISMOLOGY
  • 22
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    Detailed studies of seismicity as an indication of focal processes (1982)
    D. Reidel
    In:  Earthquake Prediction Research, Dordrecht, D. Reidel, vol. 1, no. 6, pp. 209-222
    Details
    Publication Date: 1982
    Keywords: Earthquake ; Earthquake precursor: prediction research ; Seismicity ; Fault plane solution, focal mechanism
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    BIBLIOGRAPHY SEISMOLOGY
  • 23
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    The Mammoth "Earthquake Fault" and the related features in Mono County, California (1939)
    In:  Bull. Seism. Soc. Am., Beijing, Pergamon, vol. 29, no. 3-4, pp. 333-340, pp. 1246
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Fault zone ; Geol. aspects ; Tectonics ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 24
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    Recent large earthquakes along the middle American trench and their implications for the subduction process (1982)
    In:  J. Geophys. Res., Warszawa, Conseil de l'Europe, vol. 87, no. 23, pp. 329-338, pp. 1416, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1982
    Keywords: Subduction zone ; Earthquake ; Seismicity ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 25
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    The magnitude-frequency relation as an evidence of tectonic stress with reference to the Kamchatka seismic area (1982)
    D. Reidel
    In:  Earthquake Prediction Research, Dordrecht, D. Reidel, vol. 1, no. 11, pp. 265-273, pp. 1489, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Seismology ; Magnitude ; Seismicity ; Earthquake precursor: prediction research
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    BIBLIOGRAPHY SEISMOLOGY
  • 26
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    Internally consistent pattern of seismicity near Charleston, South Carolina (1982)
    In:  Geology, Washington, D.C., AGU, vol. 10, no. E7, pp. 654-658, pp. 2568, (ISSN: 1340-4202)
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    Publication Date: 1982
    Keywords: Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 27
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    Seismic triggering and earthquake prediction (1982)
    In:  Nature, London, AGU, vol. 299, no. 2, pp. 12-13, pp. B12310, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Earthquake precursor: prediction research ; Seismicity ; Earthquake precursor: statistical anal. of seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 28
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    Earthquake activity on the North Anatolian fault zone (1982)
    Vieweg
    In:  Multidisciplinary Approach to Earthquake Prediction, Braunschweig, Vieweg, vol. 37, no. 16, pp. 95-113, (ISBN 0080419208)
    Details
    Publication Date: 1982
    Keywords: Structural geology ; Fault zone ; NAF ; Seismicity ; 1912 ; Sarköy ; Mürefte ; Sarkoy ; Muerefte ; Murefte ; West ; Marmara ; Isikara ; EAF ; FROTH ; (abstract)
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    BIBLIOGRAPHY SEISMOLOGY
  • 29
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    Some aspects of the North Anatolian fault zone derived from the comparison of its instrumental data with historical information (1982)
    Vieweg
    In:  Bull., Open-File Rept., Multidisciplinary Approach to Earthquake Prediction, Braunschweig, Vieweg, vol. 13, no. 16, pp. 223-, (ISBN 1-86239-165-3, vi + 330 pp.)
    Details
    Publication Date: 1982
    Keywords: historical ; 2000 ; years ; Seismicity ; Fault zone ; NAF ; Kolcak ; Sipahioglu ; Isikara ; FROTH ; (abstract)
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    BIBLIOGRAPHY SEISMOLOGY
  • 30
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    Faults and recently active breaks along the north Anatolian fault zone between Gerede and Ilgaz (1982)
    Vieweg
    In:  Professional Paper, Open-File Rept., Multidisciplinary Approach to Earthquake Prediction, Braunschweig, Vieweg, vol. 4, no. 16, pp. 173-, (ISBN 1-86239-165-3, vi + 330 pp.)
    Details
    Publication Date: 1982
    Keywords: Fault zone ; NAF ; turkey ; Seismicity ; Structural geology ; Earthquake ; 1943, ; 1944 ; and ; 1951 ; Isikara ; FROTH ; (abstract)
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    BIBLIOGRAPHY SEISMOLOGY
  • 31
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    Fine structure of the dipping seismic zone and subduction mechanics in the Shumagin islands, Alaska (1982)
    In:  J. Geophys. Res., Luxembourg, Conseil de l'Europe, vol. 87, no. 1-2, pp. 356-366, pp. B09402, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Subduction zone ; Seismicity ; Hypocentral depth ; Stress ; Friction ; Fracture ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 32
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    Triggering of large earthquakes by magma-chamber inflation, Izu Peninsula, Japan (1982)
    In:  Geology, London, AGU, vol. 10, no. 2, pp. 637-640, pp. B12310, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Volcanology ; Fluids ; Modelling ; Seismicity ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Stress ; Coulomb
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    BIBLIOGRAPHY SEISMOLOGY
  • 33
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    Regularity patterns and zones of seismic potential for future large earthquakes in the Mediterranean region (1982)
    In:  Tectonophys., New York, Scientific American, vol. 85, no. 20, pp. 1-30, pp. B11404, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Turkey ; Statistical investigations ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 34
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    Erdbeben (1982)
    Time-Life
    In:  Amsterdam, Time-Life, vol. 101, no. 1, pp. 1-40, (3-7723-7419-0. 319 Seiten. CD-ROM)
    Details
    Publication Date: 1982
    Keywords: Seismicity ; Textbook of geophysics ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 35
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    Displacement on the Superstition Hills fault triggered by the earthquake (1982)
    U. S. Geol. Surv.
    In:  Prof. Paper, Potsdam, U. S. Geol. Surv., vol. 10, no. 1254, pp. 145-154, (ISBN 3-933346-037)
    Details
    Publication Date: 1982
    Keywords: Fault zone ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Seismicity ; USGS
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    BIBLIOGRAPHY SEISMOLOGY
  • 36
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    Theoretische Modelle zur Reibung an Scherflächen in Gesteinen (1982)
    Inst. f. Geophysik, Ruhr-Univ. Bochum
    In:  Diplomarbeit, New York, Inst. f. Geophysik, Ruhr-Univ. Bochum, vol. C 560, 183 pp., no. GL-TR-89-0142, pp. 109-124, (ISBN 3-933346-037)
    Details
    Publication Date: 1982
    Keywords: Rock mechanics ; Seismicity ; Rheology ; Mohring
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    BIBLIOGRAPHY SEISMOLOGY
  • 37
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    Aftershocks and preearthquake seismicity - The Imperial Valley, California, earthquake of October 15, 1979 (1982)
    U. S. Geol. Surv.
    In:  Prof. Paper, Pasadena, CA., U. S. Geol. Surv., vol. C 560, 183 pp., no. 1254, pp. 59-76, (ISBN 3-933346-037)
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    Publication Date: 1982
    Keywords: Seismicity ; Aftershocks ; Fore-shocks ; USGS ; USA ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 38
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    In-flight lift and drag measurements on a first generation jet transport equipped with winglets (1982)
    In:  CASI
    Details
    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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    NASA TECHNICAL REPORTS
  • 39
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    KC-135 winglet program overview (1982)
    In:  CASI
    Details
    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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    NASA TECHNICAL REPORTS
  • 40
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    KC-135 wing and winglet flight pressure distributions, loads, and wing deflection results with some wind tunnel comparisons (1982)
    In:  CASI
    Details
    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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    NASA TECHNICAL REPORTS
  • 41
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    Turbulence amplification in shock-wave boundary-layer interaction (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Attention is directed to the acoustics research of the 1950s and 1960s for guidance in understanding and quantizing the turbulence amplification that can occur in regions of shock-wave boundary-layer interaction. Three primary turbulence amplifier-generator mechanisms are identified and shown, by linear analysis, to be responsible for turbulence amplification across a shock wave in excess of 100% of the incident turbulence intensity.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; July 198
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    NASA TECHNICAL REPORTS
  • 42
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    SPF/DB titanium concepts for structural efficiency foi HC (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Illustrations for a presentation on superplastic forming/diffusion bonding titanium design concepts are presented. Sandwich skin panels with hat section, semicircular corrugation, sine wave, and truss cores are shown. The fabrication of wing panels is illustrated, and applications to the design of advanced variable sweep bombers summarized.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Laminar Flow Control; p 95-110
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    NASA TECHNICAL REPORTS
  • 43
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    SPF/DB titanium LFC porous panel concept (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Illustrations for a presentation demonstrating superplastic forming/diffusion bonding titanium porous panels are presented. Fabrication phases, sandwich panels, load bearing qualities, microstructure, and panel surface after finishing are illustrated.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Laminar Flow Control; p 111-138
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    NASA TECHNICAL REPORTS
  • 44
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    X-29A forward-swept-wing demonstrator airplane (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The X-29A is a technology demonstrator. The FSW is just one of the technologies. Others include the following: discrete variable camber, relaxed static stability, triplex digital fly-by-wire (FBW) control system, variable-incidence/close-coupled canard, aeroelastically tailored composite wing, and thin supercritical airfoil. The growth potential for additional technologies is shown.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 177-189
    Format: text
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  • 45
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    Opportunities for wind-tunnel/flight correlation with new Boeing airplanes (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The use of correlated data in airplane development is discussed. Areas of interest include initial airworthiness of an aircraft, low-speed configuration optimization, and high-speed configuration optimization. Data from wind tunnel tests are shown to be significant when applied to guarantee compliance, which includes fuel consumption, airspeeds, and takeoff and landing performance. The use of correlation in achieving FAA certification is also discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel-Flight Correlation, 1981; p 141-157
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  • 46
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    F-15 wind-tunnel/flight correlations (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: F-15 correlation data for longitudinal control and inlet-ramp effectiveness, and horizontal-tail setting for trim are presented. The Reynolds number effect on airfoil laminar bubble burst is included.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 109-115
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  • 47
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    Wind-tunnel/flight correlation program on XB-70-1 (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The XB-70-1 was selected for a wind-tunnel/flight correlation program as representative of a large, flexible supersonic airplane similar to a supersonic transport. Tests were made to determine the effects of control deflections, wing tip deflection, and variations in inlet mass flow (additive drag).
    Keywords: AERODYNAMICS
    Type: Wind-Tunnel(Flight Correlation, 1981; p 65-91
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  • 48
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    X-29A for NTF wind-tunnel/flight correlations (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Considerations and recommendations for correlation are given. Basic tunnel calibration prior to research and development tests is suggested. Areas of concentration include: wing cruise drag and drag rise, wing separation and stall, afterbody and base drag, propulsion effects, vortex flows, cavity flows, and excrescences.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 191-197
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  • 49
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    Space-vehicle correlation of ground and flight experiments (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A 2-percent-scale model was designed for testing in the NTF. This model has remotely controlled elevons, body flap, and rudder to minimize tunnel entries associated with configuration changes in the NTF. The Shuttle Orbiter has a very large aerodynamic data base obtained in ground facilities. Since the vehicle flight-test program has already begun, a large amount of flight data can be analyzed and correlated with the NTF results.
    Keywords: AERODYNAMICS
    Type: Wind-Tunnel(Flight Correlation, 1981; p 173-176
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  • 50
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    Aerodynamic comparisons of Space Shuttle ascent: STS-1 flight versus wind-tunnel predictions (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: It is found from the comparisons that large longitudinal aerodynamic differences exist between wind tunnel predictions and flight measurements. Cold gas plume simulation underpredicted Shuttle base pressure. It is concluded that observed flight prediction increments are probably caused by several factors such as input error, independent variable errors, plume effects, and Reynolds number effects.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 133-140
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  • 51
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    Problems in correlation caused by propulsion systems (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Correlation efforts and selected results for transonic drag are reviewed. A process to reduce the typical error sources to decrease the errors inherent in the transonic aircraft development process is summarized.
    Keywords: AERODYNAMICS
    Type: Wind-Tunnel(Flight Correlation, 1981; p 93-108
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  • 52
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    Wind-tunnel/flight-drag correlation (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Predicted and flight-test drag on the C-5A and the C-141 are correlated. Equivalent rigid flight-test profile drag and a rigid estimate based on wind tunnel data are also correlated. Correlations for the National Transonic Facility are included.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 33-46
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  • 53
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    Review of the 1980 Wind-Tunnel/Flight Correlation Panel (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Wind tunnel/flight correlation history from the P-51 to the F-8 supercritical wing is reviewed, showing that researchers continue to be faced with nearly identical discrepancies in predicted versus measured drag. The capabilities of the National Transonic Facility to allow assessment of the effects which have heretofore plagued researchers and aircraft designers are anticipated.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 23-32
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  • 54
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    Transonic-flow computation using an explicit-implicit method (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The explicit-implicit predictor corrector method of MacCormack (1981) is applied to the analysis of flows past airfoils. By comparing results obtained with different methods and meshes, it is shown that the above method provides, after certain modifications, reasonably good predictions of inviscid and viscous flows about an airfoil. Good results are also obtained for the transonic regime if the free-stream conditions are correct and if a suitable mesh is used.
    Keywords: AERODYNAMICS
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  • 55
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    On the impingement of supersonic jet on a normal flat surface (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An improved method, based on one strip approximation of the method of integral relations which was reported originally by Belov, Ginzburg and Shub (1973), is presented for the calculation of flow parameters in the impingement region of a supersonic, underexpanded jet striking a normal surface located within the first cell. The results are presented for two impingement conditions and found to be in good agreement with the experimental data.
    Keywords: AERODYNAMICS
    Type: Aeronautical Quarterly; 33; Aug. 198
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  • 56
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    Pressure distributions and shock shapes for a bent-nose biconic at incidence (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Initial results of a NASA study of the lift-drag characteristics of a 12.84/7 deg biconic model intended for airbraking during atmospheric entry of probes to Mars, Venus, Saturn, and Titan are reported. Pressure distributions and shock shapes were measured in the Langley 20 in. Mach 6 tunnel with the spherically blunted bent-nose model set at angles from 0-25 deg. Pressure distributions and shock shapes where computed using the STEIN flowfield code, which features a MacCormack scheme to integrate the three-dimensional Euler equations, the Rankine-Hugoniot jump conditions to model shock waves as discontinuities, and requires a supersonic condition at every step. A comparison was made between measured and predicted values. The leeward shock angle was found to be predictable to within 3% for all angles of attack, while parabolized Navier-Stokes equations are regarded as offering more accurate results than the STEIN code for surface pressure distributions.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
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  • 57
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    Chordwise and compressibility corrections for arbitrary planform slender wings (1982)
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    Publication Date: 2011-08-18
    Description: The Lomax and Sluder method for adapting slender-wing theory to delta or rectangular wings by making chordwise and compressibility corrections is extended to cover wings of any arbitrary planform in subsonic and supersonic flows. The numerical accuracy of the present work is better than that of the Lomax-Sluder results. Comparison of the results of this work with those of the vortex-lattice method and Kernel function method for a family of Gothic and arrowhead wings shows good agreement. A universal curve is proposed for the evaluation of the lift coefficient of a low aspect ratio wing of an arbitrary planform in subsonic flow. The location of the center of pressure can also be estimated.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
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  • 58
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    Numerical investigation of turbulent channel flow (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously announced in STAR as N81-30385)
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 118; May 1982
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  • 59
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    Wind-tunnel wall interference corrections for three-dimensional flows (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A procedure for the evaluation of wall interference corrections for three-dimensional aircraft configurations is presented. The Mach number and angle-of-attack corrections are obtained by numerically solving the Laplace equation in a parallelepiped with boundary conditions supplied mainly from experimental pressure measurements. A portion of these measurements and other wind-tunnel data required by the procedure may be replaced by theoretical estimates if not available from experiments. The accuracy of the correction results will then depend on the accuracy of these estimates. The correction procedure is applied to an isolated wing and to a wing-tail configuration in a solid-wall wind tunnel. It is found that neglecting twist and camber corrections for the wing effectively increases the tail angle-of-attack correction. Two different Mach number corrections can be calculated for the wing and tail. However, since only one Mach number correction is allowed for both the wing and the tail, and since the wing surface area is larger than the tail surface area, the final correction tends to be closer to the required wing correction. This is a source of error for the tail results.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 19; June 198
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  • 60
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    Validation of LTRAN2-HI by comparison with unsteady transonic experiment (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously announced in STAR as N81-29092)
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; May 1982
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  • 61
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    Large scale model measurements of airframe noise using cross-correlation techniques (1982)
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    Publication Date: 2011-08-18
    Description: Cross-correlation techniques are used to measure the sound radiated by wing/flap airfoil configurations in the NASA-Ames 40 x 80 ft wind tunnel using a 6.7-m semispan model with three deployed flaps. The dominant source of flap noise is identified as the flap side edges, which exceeds that radiated by the midspan region by more than 10 dB. The turbulent surface eddies at the flap side edge have scales on the order of one-half the flap chord. The installation of flap actuator fairings at the flap side edge reduces the noise radiated from that location by 10 to 15 dB. The cross-correlation technique extracts airframe noise radiated by specific surface locations from the tunnel background noise, even when the noise is 25 dB higher than the measured airframe noise level.
    Keywords: AERODYNAMICS
    Type: Acoustical Society of America; vol. 71
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  • 62
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    Topological analysis of computed three-dimensional viscous flow fields (1982)
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    Publication Date: 2011-08-18
    Description: Computed solutions of the time-dependent, Reynolds-averaged Navier-Stokes equations for three-dimensional flows having thin shear layers are analyzed, using topological concepts. Specific examples include the transonic flow over a body of revolution with conical afterbody at moderate angles of incidence to the free stream. Experimental flow-visualization techniques are simulated graphically to visualize the computed flow. Scalar and vector fluid dynamic properties, such as pressure, shear stress, and vorticity on the body surface, are presented as topological maps, and their relationship to one another in terms of orientation and singular points is discussed. The extrapolation from these surface topologies toward the understanding of external flow-field behavior is discussed and demonstrated.
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  • 63
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    KC-135A Winglet Flight Flutter Program (1982)
    In:  CASI
    Details
    Publication Date: 2014-09-11
    Description: The evaluation techniques, results and conclusions for the flight flutter testing conducted on a KC-135A airplane configured with and without winglets are discussed. Test results are presented for the critical symmetric and antisymmetric modes for a fuel distribution that consisted of 10,000 pounds in each wing main tank and empty reserve tanks. The results indicated that a lightly damped oscillation was experienced for a winglet configuration of a 0 deg cant and -4 deg incidence. The effects of cant and incidence angle variation on the critical modes are also discussed. Lightly damped oscillations were not encountered for any other winglet cant and incidence angles tested.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Research Facility KC-135 Winglet Program Rev.; p 171-188
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  • 64
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    Comparison of Flight Measured, Predicted and Wind Tunnel Measured Winglet Characteristics on a KC-135 Aircraft (1982)
    In:  CASI
    Details
    Publication Date: 2014-09-11
    Description: One of the objectives of the KC-135 Winglet Flight Research and Demonstration Program was to obtain experimental flight test data to verify the theoretical and wind tunnel winglet aerodynamic performance prediction methods. Good agreement between analytic, wind tunnel and flight test performance was obtained when the known differences between the tests and analyses were accounted for. The flight test measured fuel mileage improvements for a 0.78 Mach number was 3.1 percent at 8 x 10(5) pounds W/delta and 5.5 percent at 1.05 x 10(6) pounds W/delta. Correcting the flight measured data for surface pressure differences between wind tunnel and flight resulted in a fuel mileage improvement of 4.4 percent at 8 x 10(5) pounds W/delta and 7.2 percent at 1.05 x 10(6) pounds W/delta. The performance improvement obtained was within the wind tunnel test data obtained from two different wind tunnel models. The buffet boundary data obtained for the baseline configuration was in good agreement with previous established data. Buffet data for the 15 deg cant/-4 deg incidence configuration showed a slight improvement, while the 15 deg cant/-2 deg incidence and 0 deg cant/-4 deg incidence data showed a slight deterioration.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Research Facility KC-135 Winglet Program Rev.; p 145-170
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  • 65
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    Status of NASA advanced LFC airfoil high-lift study (1982)
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    Publication Date: 2011-08-18
    Description: The design of a high lift system for the NASA advanced LFC airfoil designed by Pfenninger is described. The high lift system consists of both leading and trailing edge flaps. A 3 meter semispan, 1 meter chord wing model using the above airfoil and high lift system is under construction and will be tested in the NASA Langley 4 by 7 meter tunnel. This model will have two separate full span leading edge flaps (0.10c and 0.12c) and one full span trailing edge flap (0.25c). The performance of this high lift system was predicted by the NASA two dimensional viscous multicomponent airfoil program. This program was also used to predict the characteristics of the LFC airfoils developed by the Douglas Aircraft Company and Lockheed-Georgia Aircraft Company.
    Keywords: AERODYNAMICS
    Type: Laminar Flow Control; p 43-62
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  • 66
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    NASA Langley laminar flow control airfoil experiment (1982)
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    Publication Date: 2011-08-18
    Description: The design and construction of an advanced swept supercritical airfoil for commercial aircraft to be tested in a transonic wind tunnel is described. The swept LFC airfoil was designed for a given thickness ratio and lift coefficient, with emphasis placed on high critical Mach number with shock-free flow. It is compatible with satisfactory low speed and buffeting characteristics and minimizing the suction laminarization. Further emphasis was placed on achieving shock-free flow over a wide range of off-design conditions including trailing edge flap control. The requirements and design of the suction system and modifications to the Langley 8 foot transonic pressure tunnel is briefly described. Contouring of nonporous test section walls for free air simulation and flow quality improvements is included.
    Keywords: AERODYNAMICS
    Type: Laminar Flow Control; p 1-42
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  • 67
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    Application of Computational Fluid Dynamics (CFD) in transonic wind-tunnel/flight-test correlation (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The capability for calculating transonic flows for realistic configurations and conditions is discussed. Various phenomena which were modeled are shown to have the same order of magnitude on the influence of predicted results. It is concluded that CFD can make the following contributions to the task of correlating wind tunnel and flight test data: some effects of geometry differences and aeroelastic distortion can be predicted; tunnel wall effects can be assessed and corrected for; and the effects of model support systems and free stream nonuniformities can be modeled.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 199-215
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  • 68
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    Probability of laminar flow loss because of ice crystal encounters (1982)
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    Publication Date: 2011-08-18
    Description: A method for combining the cloud detector observation results from the Global Atmospheric Sampling Program (GASP) with Knollenberg probe observations of cloud particle concentration from other programs to derive estimates of the ambient concentration of particles larger than a given size was developed. The method was applied to estimate the probability of encountering particle concentrations which would degrade the performance of laminar flow control (LFC) aircraft. It is concluded that LF loss should occur only about one percent of the time in clear air and that flight within clouds should always result in a significant loss of LF, with 90 percent LF loss occurring about one percent of the time. Preliminary estimates of cloud encounter probability are presented for four airline routes, and conclusions are presented as to the best altitudes for cloud avoidance in extratropical and tropical latitudes.
    Keywords: AERODYNAMICS
    Type: Laminar Flow Control; p 75-94
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  • 69
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    Some ideas and opportunities concerning three-dimensional wind-tunnel wall corrections (1982)
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    Publication Date: 2011-08-18
    Description: Opportunities for improving the accuracy and reliability of wall corrections in conventional ventilated test sections are presented. The approach encompasses state-of-the-art technology in transonic computational methods combined with the measurement of tunnel-wall pressures. The objective is to arrive at correction procedures of known, verifiable accuracy that are practical within a production testing environment. It is concluded that: accurate and reliable correction procedures can be developed for cruise-type aerodynamic testing for any wall configuration; passive walls can be optimized for minimal interference for cruise-type aerodynamic testing (tailored slots, variable open area ratio, etc.); monitoring and assessment of noncorrectable interference (buoyancy and curvature in a transonic stream) can be an integral part of a correction procedure; and reasonably good correction procedures can probably be developd for complex flows involving extensive separation and other unpredictable phenomena.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 217-229
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  • 70
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    F-16E program overview and wind tunnel/flight correlation (1982)
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    Publication Date: 2011-08-18
    Description: Correlation is defined in three different ways: comparisons of wind tunnel and/or theory with flight results; detailed studies of total vehicle drag from wind tunnel and flight tests; and attempts to understand the fundamental mechanisms of fluid flows associated with aircraft components in specific areas of the flight environment. The F-16E configuration is an outgrowth of studies conducted to produce a refined fighter wing design. Several iterations required to arrive at the combination of wing planform, camber, and twist which gives near optimum lift, drag, and high-angle-of-attack stability. Theoretical analyses were backed up by extensive experimental data to validate the design and are presented
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 159-172
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  • 71
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    Aerodynamic comparisons of STS-1 Space Shuttle entry vehicle (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A conventional flight-test program, which slowly and cautiously approaches more severe flight conditions, was not possible with the Orbiter. On the first flight, the Orbiter entered the atmosphere at Mach 28 and decelerated through the Mach range. (The subsonic portion of flight was also flown by another orbiter vehicle during the Approach and Landing Test Program.) Certification for the first flight was achieved by an extensive wind-tunnel test and analysis program and by restricting the flight maneuvers severely. The initial flights of the orbiter were heavily instrumented for the purpose of obtaining accurate aerodynamic data. Even without maneuvers to excite the system, the first flight provided comparisons between flight and wind-tunnel-derived predicted data in the areas of aerodynamic performance, longitudinal trim, and reaction-control jet interaction. The aerodynamic performance comparisons are presented.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 117-131
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  • 72
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    Tunnel-to-tunnel correlation (1982)
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    Publication Date: 2011-08-18
    Description: Flow quality is discussed. Incremental comparisons of: (1) the angle of attack, (2) the axial force coefficient, and (3) the base cavity axial force coefficient against the normal force coefficient are presented. Relative blockage determination, relative buoyancy corrections, and boundary layer transition length are discussed. Blockage buoyancy caused by tunnel model wall dynamic interaction is discussed in terms of adaptive walls. The effect of 'transonic turbulence factor' is considered.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 47-63
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  • 73
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    Numerical simulation of steady supersonic flow over spinning bodies of revolution (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A recently reported parabolized Navier-Stokes code has been employed to compute the supersonic flowfield about a spinning cone and spinning and nonspinning ogive cylinder and boattailed bodies of revolution at moderate incidence. The computations were performed for flow conditions where extensive measurements for wall pressure, boundary-layer velocity profiles, and Magnus force had been obtained. Comparisons between the computational results and experiment indicate excellent agreement for angles of attack up to 6 deg. At angles greater than 6 deg discrepancies are noted which are tentatively attributed to turbulence modeling errors. The comparisons for Magnus effects show that the code accurately predicts the effects of body shape for the selected models.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Dec. 198
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  • 74
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    Numerical study of flowfields about asymmetric external conical corners (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 17, p. 3111, Accession no. A80-41562)
    Keywords: AERODYNAMICS
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  • 75
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    Wall interference evaluation from pressure measurements on control surfaces (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Conventional methods for the calculation of wall interference corrections are based on boundary conditions which require a knowledge of ventilated wall porosity parameters, and which are unsuitable for deformed walls. The method described uses a simple exponential decay of pressure distribution beyond the most upstream and downstream limits in order to evaluate Mach number and incidence corrections given by the method proposed by Papelier et al. (1978). It is found that, while the upstream contribution to incidence correction is significant, the upstream and downstream contributions to Mach number correction are negligible.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 19; Dec. 198
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  • 76
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    Airframe effects on a top-mounted fighter inlet system (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 07, p. 963, Accession no. A82-19212)
    Keywords: AERODYNAMICS
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  • 77
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    The velocity field induced by a helical vortex filament (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An exact analytical solution for the velocity field, both interior and exterior, induced by an infinite right-handed helical vortex filament is derived. Due to the way the variables combine in this solution, the paper also shows that it is possible to derive a stream function for this nonaxisymmetric flow. Sample calculations of these expressions are included.
    Keywords: AERODYNAMICS
    Type: Physics of Fluids; 25; Nov. 198
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  • 78
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    Three-dimensional shock structure in a transonic flutter cascade (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Rapid double-pulse holography was employed to obtain detailed, two-dimensional images of the shock forming during simulated flutter in a transonic flowfield. The experiment comprised a linear cascade of airfoils externally oscillated in torsion and viewed tangentially at the shock surface. Three biconvex airfoils were subjected to harmonic pitching motion about the midchord axis at a frequency of 0.53 while immersed in a Mach 0.81 flow. Failure to produce observable shocks led to use of choked flow with a Mach number near one, of which 50 holograms were taken. The images revealed a narrow shock surface with a spanwise variation in the shock properties. The method is concluded to be useful for examining transonic flowfield shocks in the presence of airfoil flutter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
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  • 79
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    Unsteady airfoils (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Progress towards successful modelling of unsteady flows past two-dimensional oscillating airfoils is examined. Linearized, thin airfoil theory is reviewed with special regard to the vortex shedding which occurs when either the body or the flow fluctuates. A sinusoidally oscillating flat-plate airfoil is considered in terms of noncirculatory components, including boundary conditions and bound and wake vortices, respectively. Applications of linear theory to vertical airfoil oscillations and to oscillating control surfaces are described, and oscillating airfoils in subsonic and supersonic flows are investigated. Perturbations in linear solutions are explored for the occurrence of second-order effects, and trailing edge and wake effects. The effects of unsteady transonic flows are broken into nearly inviscid and strongly viscous cases, and analyses of dynamic stall and stall flutter are presented.
    Keywords: AERODYNAMICS
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  • 80
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    Effect of thickness on airfoil surface noise (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Noise emission from very small chord and very large chord airfoils was measured with eleven 0.63 cm microphones placed along a horizontal semicircle (4.57 m radius) that was centered at the leading edge of the test airfoil. The noise signals were analyzed by an automated spectrum analyzer which yielded 1/3-octave band sound pressure level spectra for each microphone, and the data were corrected to remove the effects of atmospheric attenuation and jet noise. It is found that the effect of thickness is large and must be accounted for in any fundamental airfoil noise theory that attempts to describe the noise emitted from real airfoils. Incident mean velocity gradients and compressibility must also be taken into account. The effect of thickness increases with frequency, with thick airfoils being quieter than thin ones.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Mar. 198
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  • 81
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    Analysis of separated boundary-layer flows (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A method for predicting the strong interaction between the viscous and inviscid flows which occurs in flow separation is reviewed. An inverse boundary-layer procedure approximately accounts for normal pressure gradients that may be important in strongly interacting flows. Transformed boundary-layer equations are written in which the pressure gradient is set equal to the inviscid pressure gradient. As the boundary-layer edge is approached and the viscous shear and heat conduction terms vanish, the viscous flow solution is required to asymptotically approach the inviscid solution over the generalized displacement body. Attention is then focused on viscous-inviscid interacting flows with a first-order viscous formulation and constant pressure across the boundary layer. Results obtained with this procedure are presented for: (1) transitional separation bubbles near an airfoil leading edge, (2) subsonic boattail separated turbulent flow, and (3) transonic turbulent shock wave boundary-layer interaction on an axisymmetric bump configuration.
    Keywords: AERODYNAMICS
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  • 82
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    Computational aerodynamics and design (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The role of computational aerodynamics in design is reviewed with attention given to the design process; the proper role of computations; the importance of calibration, interpretation, and verification; the usefulness of a given computational capability; and the marketing of new codes. Examples of computational aerodynamics in design are given with particular emphasis on the Highly Maneuverable Aircraft Technology. Finally, future prospects are noted, with consideration given to the role of advanced computers, advances in numerical solution techniques, turbulence models, complex geometries, and computational design procedures. Previously announced in STAR as N82-33348
    Keywords: AERODYNAMICS
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  • 83
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    Three-dimensional separation and reattachment (1982)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The separation of three dimensional turbulent boundary layers from the lee of flight vehicles at high angles of attack is investigated. The separation results in dominant, large scale, coiled vortex motions that pass along the body in the general direction of the free stream. In all cases of three dimensional flow separation and reattachment, the assumption of continuous vector fields of skin friction lines and external flow streamlines, coupled with simple laws of topology, provides a flow grammar whose elemental constituents are the singular points: the nodes, spiral nodes (foci), and saddles. The phenomenon of three dimensional separation may be constrained as either a local or a global event, depending on whether the skin friction line that becomes a line of separation originates at a node or a saddle point.
    Keywords: AERODYNAMICS
    Type: AGARD High Angle-of-Attack Aerodyn.; 14 p
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  • 84
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    Three-dimensional flows about simple components at angle of attack (1982)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The structures of three dimensional separated flow about some chosen aerodynamic components at angle of attack are synthesized, holding strictly to the notion that streamlines in the external flow (viscous plus inviscid) and skin friction lines on the body surface may be considered as trajectories having properties consistent with those of continuous vector fields. Singular points in the fields are of limited number and are classified as simple nodes and saddles. Analogous flow structures at high angles of attack about blunt and pointed bodies, straight and swept wings, etc., are discussed, highlighting the formation of spiral nodes (foci) in the pattern of the skin friction lines. How local and global three dimensional separation lines originate and form is addressed, and the characteristics of both symmetric and asymmetric leeward wakes are described.
    Keywords: AERODYNAMICS
    Type: AGARD High Angle-of-Attack Aerodyn.; 56 p
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  • 85
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    Control of the forebody vortex orientation by asymmetric air injection. Part A: Application to enhance departure/spin recovery of fighter aircraft. Part B: Details of the flow structure (1982)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A novel concept which was developed to provide powerful directional control effectiveness for a fighter aircraft at high angles of attack, where more traditional controls have very limited capability is discussed. The concept utilizes the energy concentrated in the strong forebody vortices (which form on slender bodies at high relative incidence) by controlling the lateral orientation of the vortices with respect to the body. The present concept seeks to utilize the inherent sensitivity of the vortex positioning and its bistable nature to an advantage allowing control of the forces which are developed. As it turns out, the direction or sense of the asymmetric vortex pair is much easier to control than to attenuate. The work which was done to develop the concept for application to an aircraft is described and is directed toward the effects of the concept on aircraft forces and moments and on the flight mechanics of the aircraft during maneuvering at high angles of attack. The objective was to utilize the side force associated with asymmetric vortices, in a controlled manner, to enhance the ability of the fighter to recover from a departure from controlled flight. The results from these water tunnel and wind tunnel experiments show that a small amount of tangential blowing along the forebody near the apex can effectively alter the forebody vortex system and generate large restoring yawing moments.
    Keywords: AERODYNAMICS
    Type: AGARD High Angle-of-Attack Aerodyn.; 22 p
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  • 86
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    Jet V/STOL wind-tunnel simulation and groundplane effects (1982)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The pretest preparation necessary to define the objectives of an appropriate investigation into the jet V/STOL wind tunnel simulation and ground plane effects were examined. Low speed wind tunnel testing of V/STOL aircraft concepts to determine the aerodynamic propulsion interaction effects during the transition between hover and wingborne flight is a necessary step in the development cycle of this type of aircraft. Powered models are normally used to determine the aerodynamic performance characteristics. Several factors which influence the selection of the model concept and the engine simulator are discussed. Some of the test techniques important for this class of aircraft model are examined. Wind tunnel wall effects important to this aircraft testing with special emphasis on groundplane effects are reviewed.
    Keywords: AERODYNAMICS
    Type: AGARD Fluid Dyn. of Jets with Appl. to V(STOL; 21 p
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  • 87
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    Effects of the Kelvin-Helmholtz surface instability on supersonic jets (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An exact numerical calculation is provided for of linear growth and phase velocity of Kelvin-Helmholtz unstable wave modes on a supersonic jet of cylindrical cross section. An expression for the maximally unstable wavenumber of each wave mode is found. Provided a sharp velocity discontinuity exists all wave modes are unstable. A combination of rapid jet expansion and velocity shear across a jet can effectively stabilize all wave modes. The more likely case of slow jet expansion and of velocity shear at the jet surface allows wave modes with maximally unstable wavelength longer than or on the order of the jet radius to grow. The relative energy in different wave modes and effect on the jet is investigated. Energy input into a jet resulting from surface instability is discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Marshall Space Flight Center The 1982 NASA(ASEE Summer Fac. Fellowship Program; 23 p
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  • 88
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    NASA supercritical laminar flow control airfoil experiment (1982)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: The design and goals of experimental investigations of supercritical LFC airfoils conducted in the NASA Langley 8-ft Transonic Pressure Tunnel beginning in March 1982 are reviewed. Topics addressed include laminarization aspects; flow-quality requirements; simulation of flight parameters; the setup of screens, honeycomb, and sonic throat; the design cycle; theoretical pressure distributions and shock-free limits; drag divergence and stability analysis; and the LFC suction system. Consideration is given to the LFC airfoil model, the air-flow control system, airfoil-surface instrumentation, liner design and hardware, and test options. Extensive diagrams, drawings, graphs, photographs, and tables of numerical data are provided.
    Keywords: AERODYNAMICS
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  • 89
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    Application of an aerodynamic analysis method including attainable thrust estimates to low speed leading-edge flap design for supersonic cruise vehicles (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study of low speed leading-edge flap design for supersonic cruise vehicle was conducted. Wings with flaps were analyzed with the aid of a newly developed subsonic wing program which provides estimates of attainable leading-edge thrust. Results indicate that the thrust actually attainable can have a significant influence on the design and that the resultant flaps can be smaller and simpler than those resulting from more conventional approaches.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165843 , NAS 1.26:165843
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  • 90
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    Two-dimensional aerodynamic characteristics of three rotorcraft airfoils at Mach numbers from 0.35 to 0.90 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three airfoils designed for helicopter rotor application were investigated in the Langley 6- by 28-inch Transonic Tunnel to determine the two dimensional aerodynamic characteristics at Mach numbers from 0.34 to 0.88 and respective Reynolds numbers from about 4.4 x 10(6) power to 9.5 x 10(6) power. The airfoils have thickness-to-chord ratios of 0.08, 0.10, and 0.12. Trailing-edge reflex was applied to minimize pitching moment. The maximum normal-force coefficient of the RC(3)-12 airfoil is from 0.1 to 0.2 higher, depending on Mach number M, than that of the NACA 0012 airfoil tested in the same facility. The maximum normal-force coefficient of the RC(3)-10 is about equal to that of the NACA 0012 at Mach numbers to 0.40 and is higher than that of the NACA 0012 at Mach numbers above 0.40. The maximum normal force coefficient of the RC(3)-08 is about 0.19 lower than that of the NACA 0012 at a Mach number of 0.35 and about 0.05 lower at a Mach number of 0.54. The drag divergence Mach number of the RC(3)-08 airfoil at normal-force coefficients below 0.1 was indicated to be greater than the maximum test Mach number of 0.88. At zero lift, the drag-divergence Mach numbers of the RC(3)-12 and the RC(3)-10 are about 0.77 and 0.82, respectively.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2000 , L-14955 , NAS 1.60:2000 , AVRADCOM-TR-82-B-2
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  • 91
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    Wind tunnel tests of high-lift systems for advanced transports using high-aspect-ratio supercritical wings (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The wind tunnel testing of an advanced technology high lift system for a wide body and a narrow body transport incorporating high aspect ratio supercritical wings is described. This testing has added to the very limited low speed high Reynolds number data base for this class or aircraft. The experimental results include the effects on low speed aerodynamic characteristics of various leading and trailing edge devices, nacelles and pylons, ailerons, and spoilers, and the effects of Mach and Reynolds numbers.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3523 , NAS 1.26:3523 , ACEE-17-FR-1608
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  • 92
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    Pressure distribution data from tests of 2.29-meter (7.5-ft.) span EET high-lift research model in Langley 4- by 7-meter tunnel (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 2.29 m (7.5 ft.) span high-lift research model equipped with full-span leading-edge slat and part-span double-slotted trailing-edge flap was tested in the Langley 4- by 7-Meter Tunnel to determine the low speed performance characteristics of a representative high aspect ratio suprcritical wing. These tests were performed in support of the Energy Efficient Transport (EET) program which is one element of the Aircraft Energy Efficiency (ACEE) project. Static longitudinal forces and moments and chordwise pressure distributions at three spanwise stations were measured for cruise, climb, two take-off flap, and two landing flap wing configurations. The tabulated and plotted pressure distribution data is presented without analysis or discussion.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83111 , NAS 1.15:83111
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  • 93
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    Experimental studies of flow separation of three airfoils at low speeds (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests were conducted on the NASA LS(1)-0421 Mod, NACA 2412 and NASA GA(W)-2 airfoil sections at a Reynolds number of 2.2 x 10(6) and a Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers of these airfoils were obtained at pre-stall, near-stall, and post-stall angles of attack. Velocity and pressure survey results over the airfoil and in the associated wake, are presented for fully attached flow conditions through the stalled flow condition. Extensive force, pressure, tuft survey, hot-film survey, local skin friction and boundary layer data are also included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3530 , NAS 1.26:3530 , AR-79-2
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  • 94
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    The investigation of a variable camber blade lift control for helicopter rotor systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new rotor configuration called the variable camber rotor was investigated numerically for its potential to reduce helicopter control loads and improve hover performance. This rotor differs from a conventional rotor in that it incorporates a deflectable 50% chord trailing edge flap to control rotor lift, and a non-feathering (fixed) forward portion. Lift control is achieved by linking the blade flap to a conventional swashplate mechanism; therefore, it is pilot action to the flap deflection that controls rotor lift and tip path plane tilt. This report presents the aerodynamic characteristics of the flapped and unflapped airfoils, evaluations of aerodynamics techniques to minimize flap hinge moment, comparative hover rotor performance and the physical concepts of the blade motion and rotor control. All the results presented herein are based on numerical analyses. The assessment of payoff for the total configuration in comparison with a conventional blade, having the same physical characteristics as an H-34 helicopter rotor blade was examined for hover only.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3503 , NAS 1.26:3503
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  • 95
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    High Reynolds number tests of a Boeing BAC I airfoil in the Langley 0.3-meter transonic cryogenic tunnel (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation of an advanced-technology airfoil was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT). This investigation represents the first in a series of NASA/U.X. industry two dimensional airfoil studies to be completed in the Advanced Technology Airfoil Test program. Test temperature was varied from ambient to about 100 K at pressures ranging from about 1.2 to 6.0 atm. Mach number was varied from about 0.40 to 0.80. These variables provided a Reynolds number (based on airfoil chord) range from about .0000044 to .00005. This investigation was specifically designed to: (1) test a Boeing advanced airfoil from low to flight-equivalent Reynolds numbers; (2) provide the industry participant (Boeing) with experience in cryogenic wind-tunnel model design and testing techniques; and (3) demonstrate the suitability of the 0.3-m TCT as an airfoil test facility. All the objectives of the cooperative test were met. Data are included which demonstrate the effects of fixed transition, Mach number, and Reynolds number on the aerodynamic characteristics of the airfoil. Also included are remarks on the model design, the model structural integrity, and the overall test experience.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81922 , L-15011 , NAS 1.15:81922
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  • 96
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    Low-speed aerodynamic characteristics of a generic forward-swept-wing aircraft (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Low-speed wind-tunnel tests were performed on a generic forward-swept-wing aircraft model in the 7- by 10-Foot Wind Tunnel (No. 2) at Ames Research Center. The effects of various configurational changes and control-surface deflections on the performance of the model were measured. Six-component force measurements were augmented by flow-visualization photographs, using both surface oil-flow and tufts. It was found that the tendency toward premature root separation on the forward-swept wing could be reduced by use of either canards or leading-edge wing strakes and that differential canard deflections can be used to produce a direct side-force control.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 821467
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  • 97
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    Nacelle Aerodynamic and Inertial Loads (NAIL) project (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight test survey of pressures measured on wing, pylon, and nacelle surfaces and of the operating loads on Boeing 747/Pratt & Whitney JT9D-7A nacelles was made to provide information on airflow patterns surrounding the propulsion system installations and to clarify processes responsible for inservice deterioration of fuel economy. Airloads at takeoff rotation were found to be larger than at any other normal service condition because of the combined effects of high angle of attack and high engine airflow. Inertial loads were smaller than previous estimates indicated. A procedure is given for estimating inlet airloads at low speeds and high angles of attack for any underwing high bypass ratio turbofan installation approximately resembling the one tested. Flight procedure modifications are suggested that may result in better fuel economy retention in service. Pressures were recorded on the core cowls and pylons of both engine installations and on adjacent wing surfaces for use in development of computer codes for analysis of installed propulsion system aerodynamic drag interference effects.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165807 , NAS 1.26:165807 , D6-49360
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  • 98
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    Inlet design for high-speed propfans (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A two-part study was performed to design inlets for high-speed propfan installation. The first part was a parametric study to select promising inlet concepts. A wide range of inlet geometries was examined and evaluated - primarily on the basis of cruise thrust and fuel burn performance. Two inlet concepts were than chosen for more detailed design studies - one apropriate to offset engine/gearbox arrangements and the other to in-line arrangements. In the second part of this study, inlet design points were chosen to optimize the net installed thrust, and detailed design of the two inlet configurations was performed. An analytical methodology was developed to account for propfan slipstream effects, transonic flow efects, and three-dimensional geometry effects. Using this methodology, low drag cowls were designed for the two inlets.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 821359
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  • 99
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    VORCOR: A computer program for calculating characteristics of wings with edge vortex separation by using a vortex-filament and-core model (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer code base on an improved vortex filament/vortex core method for predicting aerodynamic characteristics of slender wings with edge vortex separations is developed. The code is applicable to camber wings, straked wings or wings with leading edge vortex flaps at subsonic speeds. The prediction of lifting pressure distribution and the computer time are improved by using a pair of concentrated vortex cores above the wing surface. The main features of this computer program are: (1) arbitrary camber shape may be defined and an option for exactly defining leading edge flap geometry is also provided; (2) the side edge vortex system is incorporated.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165902 , NAS 1.26:165902
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  • 100
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    Experimental trim drag values and flow-field measurements for a wide-body transport model with conventional and supercritical wings (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this study was to determine if advanced supercritical wings incur higher trim drag values at cruise conditions than current wide body technology wings. Relative trim drag increments were measured in an experimental wind tunnel investigation conducted in the Langley 8 Foot Transonic Pressure Tunnel. The tests utilized a high aspect ratio supercritical wing and a wide body aircraft wing, in conjunction with five different horizontal tail configurations, mounted on a representative wide body fuselage. The three low tail and two T-tail configurations were designed to measure the effects of horizontal tail size, location, and camber on the trim drag increments for the two wings. Longitudinal force and moment data were taken at a Mach number of 0.82 and design cruise lift coefficients for the wide body and supercritical wings of 0.45 and 0.55, respectively. The data indicate that the supercritical wing does not have significantly higher trim drag than the wide body wing. A reduction in tail size, combined with relaxed static stability, produced trim drag reductions for both wings. The cambered tails had higher trim drag increments than the symmetrical tails for both wings, and the T-tail configurations had lower trim drag increments than the low tail configurations.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2071 , L-15315 , NAS 1.60:2071
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