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  • Aerodynamics  (49)
  • Seismology  (40)
  • AERODYNAMICS  (33)
  • Animals
  • Earth model, also for more shallow analyses !
  • Fluid Mechanics and Heat Transfer
  • 1995-1999
  • 1955-1959  (126)
  • 1925-1929  (10)
  • 1958  (89)
  • 1955  (37)
  • 1927  (10)
Collection
Keywords
Publisher
Years
  • 1995-1999
  • 1955-1959  (126)
  • 1925-1929  (10)
Year
  • 1
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    Progress report, Seismological Laboratory, California Institute of Technology, 1954 (1955)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 36, no. 3-4, pp. 713-718, pp. 1246
    Details
    Publication Date: 1955
    Keywords: Seismology ; Project report/description ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    The first motion in longitudinal and transverse waves of the main shock and the direction of slip (1955)
    In:  Bull. California Division of Mines San Francisco, San Francisco, California Institute of Technology Pasadena, vol. 171, no. 6, pp. 165-170, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Waves ; Earthquake ; Body waves
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Low-velocity lithosphere channel (1955)
    In:  Bull. Geol. Soc. Am., San Francisco, California Institute of Technology Pasadena, vol. 66, no. 6, pp. 1203-1204, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Low velocity layer ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    The energy of earthquakes (1955)
    Geolog. Soc. London
    In:  Proceedings, San Francisco, Geolog. Soc. London, vol. 2, no. 6, pp. 1530, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Energy (of earthquakes)
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Larger shocks of 1954 (1955)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, San Francisco, California Institute of Technology Pasadena, vol. 1954, no. 6, pp. 112, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Untersuchungen zur Bodenunruhe in Süd-Kalifornien (1955)
    In:  Zeitschrift für Geophysik, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 21, no. 6, pp. 177-189, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; NOISE
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Seismograph stations in California (1955)
    In:  Bull. California Division of Mines, San Francisco, California Institute of Technology Pasadena, vol. 171, no. 6, pp. 153-156, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Instruments ; Seismometer
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Magnitude determination for larger Kern County shocks, 1952; effects of station azimuth and calculation methods (1955)
    In:  Bull. California Division of Mines San Francisco, San Francisco, California Institute of Technology Pasadena, vol. 171, no. 6, pp. 171-175, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Magnitude ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Channel waves in the earth's crust (1955)
    In:  Bull. Geol. Soc. Am., San Francisco, California Institute of Technology Pasadena, vol. 66, no. 6, pp. 1651, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Channel waves ; CRUST ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Energy of earthquakes (1955)
    In:  Science, San Francisco, California Institute of Technology Pasadena, vol. 122, no. 6, pp. 876, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Energy (of earthquakes)
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Magnitude and energy: progress report (1955)
    In:  Bull. Geol. Soc. Am., San Francisco, California Institute of Technology Pasadena, vol. 66, no. 6, pp. 1651, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Magnitude ; Energy (of earthquakes) ; Seismology ; Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Magnitude and energy of earthquakes (1955)
    In:  Nature, San Francisco, California Institute of Technology Pasadena, vol. 176, no. 6, pp. 795, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Magnitude ; Energy (of earthquakes)
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    The structure of the earth as viewed 1957 (1958)
    In:  Scientia, Milano, Academic Press, vol. 93 (=52), no. 6, pp. 1-5, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Earth model, also for more shallow analyses ! ; Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Two types of microseisms (1958)
    In:  Journ. Geophys. Res., New York, Academic Press, vol. 63, no. 6, pp. 595-597, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Micro seismicity ; Seismology ; NOISE ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Spectrum of P and S in records of distance earthquakes (1958)
    In:  Bull. Geol. Soc. Am., Milano, Academic Press, vol. 69, no. 6, pp. 1686, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Seismology ; Spectrum ; Body waves ; Teleseismic events
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Attenuation of seismic waves in the earth's mantle (1958)
    In:  Bull. Geol. Soc. Am., Milano, Academic Press, vol. 69, no. 6, pp. 1686, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Attenuation ; Seismology ; earth mantle
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    Velocity of seismic waves in the earth's mantle (1958)
    In:  Bull. Geol. Soc. Am., Milano, Academic Press, vol. 69, no. 6, pp. 1686, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Velocity analysis ; Seismology ; earth mantle
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    BIBLIOGRAPHY SEISMOLOGY
  • 18
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    A note on the theory of the electromagnetic seismograph (1958)
    In:  Bull. Earthquake Res. Inst. Tokyo Univ., Warszawa, Eötvös Lorand Geophysical Institute of Hungaria, vol. 36, no. 49, pp. 139-164, pp. 2342, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Seismology ; Instruments
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    BIBLIOGRAPHY SEISMOLOGY
  • 19
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    The nature of seismic origins as inferred from seismological and geodetic observations (2) (1958)
    In:  Bull. Earthqu. Res. Inst., Tokyo Univ., Amsterdam, Elsevier Scientific Publishing Company, vol. 36, no. 5580, pp. 21-53, pp. 1012, (ISSN: 1340-4202)
    Details
    Publication Date: 1958
    Keywords: Seismology ; Dislocation ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Geodesy
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    BIBLIOGRAPHY SEISMOLOGY
  • 20
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    Properties of strong ground motion earthquakes (1955)
    In:  Bull. Seism. Soc. Am., Berlin, Ges. f. Geowissenschaften e.V., vol. 45, no. 5454, pp. 197-218, pp. L02309, (ISSN 0343-5164)
    Details
    Publication Date: 1955
    Keywords: Strong motions ; Seismology ; Dislocation ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 21
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    Energy release in earthquakes (1958)
    In:  Geophys. J., New York, Conseil de l'Europe, vol. 1, no. 2, pp. 44-52, pp. B07307, (ISSN: 1340-4202)
    Details
    Publication Date: 1958
    Keywords: Seismology ; seismic Moment ; Elasticity ; Source ; Energy (of earthquakes) ; Two-dimensional ; Dislocation ; FROTH ; MSOBIESIAK
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    BIBLIOGRAPHY SEISMOLOGY
  • 22
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    Die Veränderung der Erdkruste durch Fließbewegungen der Kontinentalscholle (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 16, no. 3, pp. 239-247, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; Tectonics ; Inelastic ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 23
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    Der Aufbau der Erdkruste (1927)
    In:  Zeitschrift für Geophysik, Jena, Gustav Fischer, vol. 3, no. 3, pp. 371-377, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; CRUST
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    BIBLIOGRAPHY SEISMOLOGY
  • 24
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    Die Bodenunruhe durch Brandung (1927)
    In:  Zeitschrift für Geophysik, Jena, Gustav Fischer, vol. 3, no. 3, pp. 328-329, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: NOISE ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 25
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    Die Veränderung der Erdkruste durch Fließbewegungen II (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 18, no. 3, pp. 281-291, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; Tectonics ; Inelastic ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 26
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    Wave velocities in the earth's crust (1955)
    Geol. Soc. Am.
    In:  Professional Paper, The earth's crust - a symposium, Berlin, Geol. Soc. Am., vol. 62, no. XVI:, pp. 19-34, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1955
    Keywords: Velocity analysis ; CRUST ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 27
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    Magnitude, statistics, energy (1958)
    Freeman
    In:  Bull., Open-File Rept., Elementary Seismology, San Francisco, Cal., Freeman, vol. 78, no. 87-17, pp. 338-349, (ISBN 0080419208)
    Details
    Publication Date: 1958
    Keywords: Textbook of geophysics ; Seismology ; Magnitude ; Energy (of earthquakes) ; Statistical investigations ; Scaling
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    BIBLIOGRAPHY SEISMOLOGY
  • 28
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    Why all this interest in the shape of the pulse ? (1958)
    In:  Geophys. Prosp., Amsterdam, Elsevier Scientific Publishing Company, vol. 6, no. 12, pp. 394-403, pp. L23303
    Details
    Publication Date: 1958
    Keywords: Discrimination ; Seismology ; Seismics (controlled source seismology) ; Deconvolution
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    BIBLIOGRAPHY SEISMOLOGY
  • 29
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    A note on the seismic pulse recorded from a mine explosion (1958)
    In:  Geophys. Prosp., Amsterdam, Elsevier Scientific Publishing Company, vol. 6, no. 12, pp. 433-437, pp. L23303
    Details
    Publication Date: 1958
    Keywords: Nuclear explosion ; Seismology ; Source ; Discrimination
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    BIBLIOGRAPHY SEISMOLOGY
  • 30
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    Progress report, Seismological Laboratory, California Institute of Technology, 1957 (1958)
    In:  Trans. Am. Geophys. Union, San Francisco, Pergamon, vol. 39, no. 3-4, pp. 721-725, pp. 1246
    Details
    Publication Date: 1958
    Keywords: Seismology ; Project report/description ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 31
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    Channel waves in the earth's crust (1955)
    In:  Geophysics, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 20, no. 6, pp. 283-294, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1955
    Keywords: Channel waves ; CRUST ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 32
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    Velocity of seismic waves in the earth's mantle (1958)
    In:  Trans., Am. Geophys. Union, Rome, California Institute of Technology Pasadena, vol. 39, no. 6, pp. 486-489, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Velocity analysis ; Seismology ; earth mantle ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 33
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    Caustics produced by waves through the earth's core (1958)
    In:  Geophys. Journ. Royal astr. Soc., Rome, California Institute of Technology Pasadena, vol. 1, no. 6, pp. 238-248, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: earth Core ; Waves ; Seismology ; Wave propagation ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 34
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    Wave velocities in the earth's core (1958)
    In:  Bull. Seism. Soc. Am., Rome, California Institute of Technology Pasadena, vol. 48, no. 6, pp. 301-314, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Velocity analysis ; earth Core ; Earth model, also for more shallow analyses ! ; Seismology ; Velocity depth profile ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 35
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    Microseisms (1958)
    Academic Press
    In:  Advances in Geophysics, New York, Academic Press, vol. 5, no. 6, pp. 53-92, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Micro seismicity ; Seismology ; NOISE
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    BIBLIOGRAPHY SEISMOLOGY
  • 36
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    Attenuation of seismic waves in the earth's mantle (1958)
    In:  Bull. Seism. Soc. Am., Rome, California Institute of Technology Pasadena, vol. 48, no. 6, pp. 269-282, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1958
    Keywords: Attenuation ; Seismology ; earth mantle ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 37
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    General introduction to seismology (1955)
    In:  Bull. California Division of Mines, San Francisco, Pergamon, vol. 171, no. 3-4, pp. 131-135, pp. 1246
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Review article
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  • 38
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    Die Veränderung der Erdkruste durch Fließbewegungen der Kontinentalscholle (1927)
    In:  Geologische Rundschau, Jena, Gustav Fischer, vol. 18, no. 3, pp. 148-149, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; Tectonics ; Inelastic ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 39
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    Die Geschwindigkeit der Longitudinalwellen im Erdinnern (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 17, no. 3, pp. 356-365, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Travel time ; Earth model, also for more shallow analyses ! ; Seismology ; Body waves ; Velocity depth profile
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    BIBLIOGRAPHY SEISMOLOGY
  • 40
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    Die Herdtiefe der Süddeutschen Beben 1911 und 1913 (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 18, no. 3, pp. 379-382, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earthquake ; Hypocentral depth ; Seismology
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  • 41
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    Erdbeben und Erdbebenwellen (1927)
    J. A. Barth
    In:  Professional Paper, Handbuch der physikalischen und technischen Mechanik, Bd. III, Leipzig, J. A. Barth, vol. 3, no. VIIa, pp. 387-420, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1927
    Keywords: Seismology ; Seismicity ; Waves
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    BIBLIOGRAPHY SEISMOLOGY
  • 42
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    Grundlagen der Erdbebenkunde (1927)
    Bornträger
    In:  Berlin, Bornträger, vol. 12, 189 S., no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1927
    Keywords: Textbook of geophysics ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 43
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    Elementary Seismology (1958)
    Freeman
    In:  San Francisco, Cal., 768 pp., Freeman, vol. 121, no. Publ. No. 12, pp. 127, (ISBN 0-521-66034-3, ISBN 0-521-66948-0 paper)
    Details
    Publication Date: 1958
    Keywords: Textbook of geophysics ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 44
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    Epicenter and origin time of the main shock on July 21 and travel times of major phases (1955)
    California Division of Mines San Francisco
    In:  Bull., Earthquakes in Kern County, California during 1952, Berlin, California Division of Mines San Francisco, vol. 171, no. XVI:, pp. 157-163, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1955
    Keywords: Seismology ; Seismicity ; Earthquake ; Travel time
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    BIBLIOGRAPHY SEISMOLOGY
  • 45
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    Appendix part III: VIII. Transit-Time Tables, Magnitude Charts (1958)
    Freeman
    In:  Bull., Open-File Rept., Elementary Seismology, San Francisco, Cal., Freeman, vol. 78, no. 87-17, pp. 687-690, (ISBN 0080419208)
    Details
    Publication Date: 1958
    Keywords: Textbook of geophysics ; Seismology ; Travel time ; Magnitude
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    BIBLIOGRAPHY SEISMOLOGY
  • 46
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    Rheological problems of the earth's interior (1958)
    Academic Press
    In:  Bull., Polar Proj. OP-O3A4, Rheology: Theory and Applications Vol. 2, New York, Academic Press, vol. 18, no. XVI:, pp. 401-431, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1958
    Keywords: Earth model, also for more shallow analyses ! ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 47
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    THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (1958)
    In:  Other Sources
    Details
    Publication Date: 2011-08-10
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 48
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    Some effects of flow spoilers and of aerodynamic balance on the oscillating hinge moments for a swept fin-rudder combination in a transonic wind tunnel (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Flow spoiler and aerodynamic balance effects on oscillating hinge moments for swept fin-rudder combination in transonic wind tunnel
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C28
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 49
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    Investigation of an all-movable control surface at a mach number of 6.86 for possible flutter (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Movable tail surface for aircraft control without flutter using X-15 scale model at hypersonic speed
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58B27
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 50
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    Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested we re a body alone which had a ratio of length to diameter of 10, the b ody with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose. Various canard surfaces for pitch control only were te sted on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.
    Keywords: AERODYNAMICS
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  • 51
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    Performance of multiple jet-exit installations (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Internal aerodynamics and performance of clustered jet-exit installations at transonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58E01
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  • 52
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    An Investigation of the Effects of Nose and Lip Shapes for an Underslung Scoop Inlet at Mach Numbers from 0 to 1.9 (1955)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6 to 1.9 over a large positive angle-of-attack range without adverse effects on the pressure recovery. Although there was no one inlet configuration that was markedly superior over the entire range of operating variables, the arrangement having a nose designed to give increased supersonic compression at low angles of attack, and a sharp lip (configuration designated N3L3) showed the most favorable performance characteristics over the supersonic Mach number range. Inlets with sizable lip radii gave satisfactory performance up to a Mach number of 1.5; however, as a result of an increase in drag, the performance of such inlets was markedly inferior to the sharp-lip configuration above Mach numbers of 1.5. Throughout the range of test Mach numbers all inlet configurations evidenced stable air-flow characteristics over the mass-flow range for normal engine operation. Analysis of the inlet performance on the basis of a propulsive thrust parameter showed that a fixed inlet area could be used for Mach numbers up to 1.5 with only a small sacrifice in performance.
    Keywords: AERODYNAMICS
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  • 53
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    Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Supersonic pressure distributions for tip and trailing edge controls on 60 deg delta wing
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C07
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  • 54
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    Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Horizontal tail flutter in fighter aircraft at transonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57K13
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  • 55
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    Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile with Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected. Directional stability data were obtained at M=3.51 for angles of attack of approximately 0 deg and 10 deg. These data, with summary data and typical schlieren photographs, are presented with only a brief analysis. The data indicate that the controls are effective throughout the Mach number range and lift-coefficient range (CL = -0.15 to 0.7, approximately) of the tests. There is a severe break in the pitching-moment curve at M=2.29 which might result in a pitch-up condition in flight, and also a large forward movement of the aerodynamic center with increasing Mach number that produces neutral longitudinal stability at M=3.51 for the moment center used in this investigation. The model was directionally unstable at M=3.51; however, the level of directional stability was about the same for 0 deg and 10 deg angles of attack.
    Keywords: AERODYNAMICS
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  • 56
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    Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-tail Component Drag of a Twin-engine Fighter-type Airplane Model (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C04
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  • 57
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    Experimental and Analytical Investigation of the Transonic and Supersonic Divergence Characteristics of a Delta-Plan-Form All- Movable Control (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: The static aeroelastic divergence characteristics of a delta-planform model of the canard control surface of a proposed air-to-ground missile have been studied both analytically and experimentally in the Mach number range from 0.6 to 3.0. The experiments indicated that divergence occurred at a nearly constant value of dynamic pressure at Mach numbers up to 1.2. At higher Mach numbers somewhat higher values of dynamic pressure were required to produce divergence. The analysis and the experiment indicate that the camber stiffness of the control surface and the stiffness of the control actuator are both important in divergence of surfaces of this type.
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58E07
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  • 58
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    Preliminary transonic performance results for solid and slotted turbojet nacelle afterbodies incorporating fixed divergent jet nozzles designed for supersonic operation (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Transonic performance of three turbojet nozzle- afterbody configurations
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-24-58L
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  • 59
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    Free-flight investigation of the drag of a 60 deg delta-wing configuration with large stores mounted below the indented fuselage at mach numbers between 0.8 and 1.6 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Free flight drag measurements on delta wing with wing-fuselage-store
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-9-58L
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  • 60
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    Use of stage-stacking technique for predict- ing over-all performance in multistage axial- flow compressor utilizing interstage-air bleed (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Stage-stacking technique for predicting over-all performance in multistage axial flow turbojet compressor using interstage-air bleed
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-4-58E
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  • 61
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    High mach number, low-cowl-drag, external- compression inlet with subsonic dump diffuser (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application
    Keywords: AERODYNAMICS
    Type: NACA-RM-E58A09
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  • 62
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    Experimental investigation of a high subsonic mach number turbine having a 40-blade rotor with zero suction-surface diffusion (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Experimental investigation of high subsonic turbine with forty blade rotor with zero suction-surface diffusion
    Keywords: AERODYNAMICS
    Type: NACA-RM-E57J22
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  • 63
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    An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Static longitudinal stability and control characteristics of wingless missile configuration at supersonic and hypersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A58C20
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  • 64
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    Exploratory Wind-Tunnel Investigation to Determine the Lift Effects of Blowing over Flaps from Nacelles Mounted Above the Wing (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An exploratory wind-tunnel investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3. Several flap conditions were examined. High-pressure air was blown from an external-pipe arrangement supported above the wing to simulate jet-engine exhaust. The jet momentum- coefficient range was from 0 to 3.0 and the model angle of attack was 0 deg. The results of this limited investigation show that values of jet circulation lift coefficient larger than the Jet reaction were produced with blowing over flaps from nacelles mounted above the wing. 'I!heuse of double slotted flaps with the gap unsealed between the flaps and wing had a large detrimental effect on the lift capabilities. With these gaps sealed, larger lift coefficients were obtained when fantails were added to the nacelles. The longitudinal trim problems created by large diving moments were similar to those encountered with other jet-augmented-flap systems
    Keywords: Aerodynamics
    Type: NACA-TN-4298
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  • 65
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    Theoretical Calculations of Supersonic Wave Drag at Zero Lift for a Particular Store Arrangement (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis, based on the linearized thin-airfoil theory for supersonic speeds, of the wave drag at zero lift has been carried out for a simple two-body arrangement consisting of two wedgelike surfaces, each with a rhombic lateral cross section and emanating from a common apex. Such an arrangement could be used as two stores, either embedded within or mounted below a wing, or as auxiliary bodies wherein the upper halves could be used as stores and the lower halves for bomb or missile purposes. The complete range of supersonic Mach numbers has been considered and it was found that by orienting the axes of the bodies relative to each other a given volume may be redistributed in a manner which enables the wave drag to be reduced within the lower supersonic speed range (where the leading edge is substantially subsonic). At the higher Mach numbers, the wave drag is always increased. If, in addition to a constant volume, a given maximum thickness-chord ratio is imposed, then canting the two surfaces results in higher wave drag at all Mach numbers. For purposes of comparison, analogous drag calculations for the case of two parallel winglike bodies with the same cross-sectional shapes as the canted configuration have been included. Consideration is also given to the favorable (dragwise) interference pressures acting on the blunt bases of both arrangements.
    Keywords: Aerodynamics
    Type: NACA-TN-4120
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  • 66
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    The Compressible Laminar Boundary Layer with Fluid Injection (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A solution of the equations of the compressible laminar boundary layer including the effects of transpiration cooling is presented. The analysis applies to the flow over an isothermal porous plate with a velocity of fluid injection proportional to the reciprocal of the square root of the distance from the leading edge. The effect of several flow parameters on coolant-flow rates is discussed with the aid of representative examples. A stability analysis indicates that, although transpiration cooling requires a lower surface temperature for stable flow than does internal wall cooling, this lower temperature can be obtained with a smaller expenditure of coolant.
    Keywords: Aerodynamics
    Type: NACA-TN-3404
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  • 67
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    Behavior of a Cantilever Plate Under Rapid-heating Conditions (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The temperature distributions encountered in thin solid wings subjected to aerodynamic heating induce thermal stresses that may effectively reduce the stiffness of the wing. The effects of this reduction in stiffness were investigated experimentally by rapidly heating the edges of a cantilever plate. The midplane thermal stresses imposed by the nonuniform temperature distribution caused the plate to buckle torsionally, increased the deformations of the plate under a constant applied torque, and reduced the frequency of the first two natural modes of vibration. By using small-deflection theory and employing energy methods, the effect of nonuniform heating on the plate stiffness was calculated. The theory predicts the general effects of the thermal stresses, but becomes inadequate as the temperature difference increases and plate deflections become large.
    Keywords: Aerodynamics
    Type: NACA-RM-L55E20c
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  • 68
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    Heat-Transfer Measurements in Free Flight at Mach Numbers up to 14.6 on a Flat-Faced Conical Nose with a Total Angle of 29 Degrees (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Skin-temperature measurements have been made at several locations on a flat-faced cone-cylinder nose which was flight tested on a fivestage rocket-propeller model to a Mach number of 14.64 and a free-stream Reynolds number of 2.0 x 10(exp 6), based on flat-face diameter, at an altitude of 66,300 feet. The copper nose had a 29 deg total-angle conical section which was 1.6 flat-face diameters long. The aerodynamic-heating rates determined from the temperature measurements reached 1,440 Btu/( sec) (sq ft) on the flat face. The heating rates near the center of the flat face agreed well at Mach numbers up to 13.6 with those obtained by a theory for laminar stagnation-point heating in equilibrium dissociated air (Avco Res. Rep. 1). At Mach numbers above 13.6, the heating rates at locations near the center of the flat face became progressively lower than stagnation-point theory and. were 29 percent lower at Mach number 14.6 at the end. of the test. The reason for this behavior of the heating on the central part of the flat face was not determined. Excluding the relatively low heating rates that occurred on the central part of the nose at the highest Mach numbers, the distribution of experimental heating along the innermost 0.79 of the flat-face radius, expressed as a percentage of stagnation-point heating, was in fair agreement with the distribution predicted by laminar theory. At a location of 0.71 radii from the stagnation point, the experimental heating was very near 130 percent of the theoretical stagnation-point rate at Mach numbers from 11 to 14.5. The experimental beating rates on the conical section of the nose were in good agreement with laminar-cone theory using the assumption of theoretical sharp-cone static pressure on the conical section.
    Keywords: Aerodynamics
    Type: NACA-RM-L57L03
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  • 69
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    Flow and Drag Formulas for Simple Quadrics (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives the pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. For the cases treated the concordance of theory and measurement is so close as to make a resume of results desirable. Incidentally formulas for the velocity at all points of the flow field are given, some being new forms for ready use derived in a previous paper. (author)
    Keywords: Aerodynamics
    Type: NACA-TR-253
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  • 70
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    Approximate Solutions for the Flow About Flat-Top Wing-Body Configurations at High Supersonic Airspeeds (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: The flow about slender flat-top wing-body configurations traveling at high supersonic speeds and small angles of attack is investigated analytically. In the case of conical configurations, approximate algebraic solutions to the flow field are obtained. In the case of configurations which are conical at the vertex but curved in the stream direction, these solutions are combined with a slender-body approximation to the generalized shock-expansion method to obtain the flow downstream of the vertex. Surface pressures were obtained experimentally at Mach numbers from 3.0 to 6.0 and angles of attack up to 6 deg for several flat-top wing-body configurations. These configurations consisted of half-bodies of revolution mounted beneath thin highly swept wings. Three different bodies were employed. The two conical bodies consisted of one-half of a fineness-ratio-5 cone and one-half of a fineness-ratio-2-1/2 cone. The body of the third configuration consisted of one-half of a fineness-ratio-5 ogive. For the ogive configuration, the leading edges of the wing were curved and designed to just maintain the theoretically determined bow shock along the leading edge at a Mach number of 5.0 and an angle of attack of 3 deg. The predictions of the conical flow theory of this paper for the surface pressures are found to be in good agreement with experiment at Mach numbers of 5.0 and 6.0 up to angles of attack of approximately 3 deg. Estimated lift, drag, and pitching-moment coefficients, as well as maximum lift-drag ratio, are also in good agreement with existing experimental data at a Mach number of 5.0 for a conical configuration having an arrow plan-form wing. It is also found that the generalized shock-expansion method yields reasonable good agreement with experiment for the surface pressures on the half-ogive configuration at a Mach number of 5.0 and an angle of attack of 3 deg.
    Keywords: Aerodynamics
    Type: NACA-RM-A58F02
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  • 71
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    Tabulated Data From a Pressure-Distribution Investigation at Mach Number 2.01 of a 45 Deg Sweptback-Wing Airplane Model at Combined Angles of Attack and Sideslip (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: A pressure-distribution investigation of a wing-body combination has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01. The model configuration consisted of an ogive-circular-cylinder body (fineness ratio of approximately ii) and a wing with 45 deg of sweepback at the quarter-chord line, an aspect ratio of 4, and a taper ratio of 0.2. Data were obtained on high-, mid-, and low-wing configurations and for the body and wing alone for a range of angles of attack and yaw from 0 deg to 15 deg. The tabulated pressure coefficients are presented in this report.
    Keywords: Aerodynamics
    Type: NASA-MEMO-10-15-58L
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  • 72
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    Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line.
    Keywords: Aerodynamics
    Type: NACA-RM-L58G03
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  • 73
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    Boundary-Layer-Transition Measurements in Full-Scale Flight (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages installed in a Fiberglas "glove" installation on one wing. Tests were conducted at speeds from a Mach number of 1.2 to a Mach number of 2.0, at altitudes from 35,000 feet to 56,000 feet. Data obtained at all angles of attack, from near 0 deg to near 10 deg, have shown that the maximum transition Reynolds number on the upper surface of the wing varies from about 2.5 x 10(exp 6) at a Mach number of 1.2 to about 4 x 10(exp 6) at a Mach number of 2.0. On the lower surface, the maximum transition Reynolds number varies from about 2 x 10(exp 6) at a Mach number of 1.2 to about 8 x 10(exp 6) at a Mach number of 2.0.
    Keywords: Aerodynamics
    Type: NACA-RM-H58E28
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  • 74
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    Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Transonic flutter characteristics of sweptback fighter airplane wing models
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58A15
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  • 75
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    Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight (1955)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Aircraft body flare for pitch stability and body flap for pitch control in hypersonic flight
    Keywords: AERODYNAMICS
    Type: NACA-RM-A54J13
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  • 76
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    Effects of modifications to a control surface on a 6-percent-thick unswept wing on the transonic control-surface flutter derivatives (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements
    Keywords: AERODYNAMICS
    Type: NACA-RM-A58B04
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  • 77
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    Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Deg Swept- Wing-Fuselage Configuration at a Mach Number of 1.61 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57K18
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  • 78
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    Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7
    Keywords: AERODYNAMICS
    Type: NACA-RM-E58E16
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  • 79
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    Investigation of Inlet Control Parameters for an External-internal-compression Inlet from Mach 2.1 to 3.0 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned.
    Keywords: AERODYNAMICS
    Type: NACA-RM-E58G08
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  • 80
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    Exploratory wind-tunnel investigation to determine the lift effects of blowing over flaps from nacelles mounted above the wing (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-TN-4298
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  • 81
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    A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possibility of drag reduction for a particular case. The model considered consists of a body of revolution in combination with any wing that has an unswept trailing edge and a constant trailing-edge angle along its span. It is found that (neglecting any change in base drag) a drag reduction is obtainable which, for the case considered, is an additional 12 percent of that obtained with the area-rule modification. The probable effect of viscosity on this theoretical result is discussed.
    Keywords: AERODYNAMICS
    Type: NACA-TN-4277
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  • 82
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    The icing problem: Current status of NACA techniques and research (1955)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: AGARD-AG-19/P9
    Format: text
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  • 83
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    An investigation of supersonic store interference in the vicinity of a 22 deg swept wing fuselage configuration at Mach numbers of 1.61 and 2.01 (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure tunnel investigation of supersonic store interference in vicinity of 22 deg swept wing fuselage configuration at mach numbers 1.61 and 2.01
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57L18
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  • 84
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    A Flight Evaluation and Analysis of the Effect of Icing Conditions on the ZPG-2 Airship (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of test flights was conducted by the U. S. Navy over a 3- year period to evaluate the effects of icing on the operation of the ZPG-2 airship. In supercooled. clouds, ice formed only on the forward edges of small protuberances and wires and presented no serious hazard to operation. Ice accretions of the glaze type which occurred in conditions described as freezing drizzle adversely affected various components to a somewhat greater extent. The results indicated, a need for protection of certain components such as antennas, propellers, and certain parts of the control system. The tests showed that icing of the large surface of the envelope occurred only in freezing rain or drizzle. Because of the infrequent occurrence of these conditions, the potential maximum severity could not be estimated from the test results. The increases in heaviness caused by icing in freezing rain and drizzle were substantial, but well within the operational capabilities of the airship. In order to estimate the potential operational significance of icing in freezing rain, theoretical calculations were used to estimate: (1) the rate of icing as a function of temperature and rainfall intensity, (2) the climatological probability of occurrence of various combinations of these variables, and (3) the significance of the warming influence of the ocean in alleviating freezing-rain conditions. The results of these calculations suggest that, although very heavy icing rates are possible in combinations of low temperature and high rainfall rate, the occurrence of such conditions is very infrequent in coastal areas and virtually impossible 200 or 300 miles offshore.
    Keywords: AERODYNAMICS
    Type: NACA-TN-4220
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  • 85
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    Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An empirical relation has been obtained by which the change in drag coefficient caused by ice formations on an unswept NACA 65AO04 airfoil section can be determined from the following icing and operating conditions: icing time, airspeed, air total temperature, liquid-water content, cloud droplet impingement efficiencies, airfoil chord length, and angles of attack. The correlation was obtained by use of measured ice heights and ice angles. These measurements were obtained from a variety of ice formations, which were carefully photographed, cross-sectioned, and weighed. Ice weights increased at a constant rate with icing time in a rime icing condition and at progressively increasing rates in glaze icing conditions. Initial rates of ice collection agreed reasonably well with values predicted from droplet impingement data. Experimental droplet impingement rates obtained on this airfoil section agreed with previous theoretical calculations for angles of attack of 40 or less. Disagreement at higher angles of attack was attributed to flow separation from the upper surface of the experimental airfoil model.
    Keywords: AERODYNAMICS
    Type: NACA-TN-4151
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  • 86
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    Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions. In general, icing of the airfoil at angles of attack less than 40 caused large increases in section drag coefficients (as much as 350 percent in 8 minutes of heavy glaze icing), reductions in section lift coefficients (up to 13 percent), and changes in the pitching-moment coefficient from diving toward climbing moments. At angles of attack greater than 40 the aerodynamic characteristics depended mainly on the ice type. The section drag coefficients generally were reduced by the addition of rime ice (by as much as 45 percent in 8 minutes of icing). In glaze icing, however, the drag increased at these angles of attack. The section lift coefficients were variably affected by rime-ice formations; however, in glaze icing, lift increases at high angles of attack amounted to as much as 9 percent for an icing time of 8 minutes. Pitching-moment-coefficient changes in icing conditions were somewhat erratic and depended on the icing condition. Rotation of the iced airfoil to angles of attack other than that at which icing occurred caused sufficiently large changes in the pitching-moment coefficient that, in flight, rapid corrections in trim might be required in order to avoid a hazardous situation.
    Keywords: AERODYNAMICS
    Type: NACA-TN-4155
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  • 87
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    Icing limit and wet-surface temperature variation for two airfoil shapes under simulated high-speed flight conditions (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-TN-3396
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  • 88
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    A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79843 , NACA-TR-1349 , NACA-TN-3858
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  • 89
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    Aerodynamic Research on Fuselages with Rectangular Cross Section (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The influence of the deflected flow caused by the fuselage (especially by unsymmetrical attitudes) on the lift and the rolling moment due to sideslip has been discussed for infinitely long fuselages with circular and elliptical cross section. The aim of this work is to add rectangular cross sections and, primarily, to give a principle by which one can get practically usable contours through simple conformal mapping. In a few examples, the velocity field in the wing region and the induced flow produced are calculated and are compared with corresponding results from elliptical and strictly rectangular cross sections.
    Keywords: Aerodynamics
    Type: NACA-TM-1414 , Jahrbuch 1942 der Deutschen Luftfahrtforschung; 263-279
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  • 90
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    Preliminary Results of the Determination of Inlet-Pressure Distortion Effects on Compressor Stall and Altitude Operating Limits of the J57-P-1 Turbojet Engine (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the high- and low-speed engine operating limits were investigated up to the maximum operable altitude. The effect of changing the compressor bleed position on the stall and operating limits was determined for one of the inlet distortions. The circumferential distortions lowered the compressor stall pressure ratios; this resulted in less fuel-flow margin between steady-state operation and compressor stall. Consequently, the altitude operating Limits with circumferential distortions were reduced compared with the uniform inlet profile. Radial inlet-pressure distortions increased the pressure ratio required for compressor stall over that obtained with uniform inlet flow; this resulted in higher altitude operating limits. Likewise, the stall-limit fuel flows required with the radial inlet-pressure distortions were considerably higher than those obtained with the uniform inlet-pressure profile. A combined radial-circumferential inlet distortion had effects on the engine similar to the circumferential distortion. Bleeding air between the two compressors eliminated the low-speed stall limit and thus permitted higher altitude operation than was possible without compressor bleed.
    Keywords: Aerodynamics
    Type: NACA-RM-SE55E23
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  • 91
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    An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A linear stability analysis and flight-test investigation has been performed on a rolleron-type roll-rate stabilization system for a canard-type missile configuration through a Mach number range from 0.9 to 2.3. This type damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by the introduction of control-surface damping about the rolleron hinge line. The control-surface damping was provided by an orifice-type damper contained within the control surface. Steady-state rolling velocities were at all times less than 1 radian per second between the Mach numbers of 0.9 to 2.3 on the configurations tested. No adverse longitudinal effects were experienced in flight because of the tendency of the free-floating rollerons to couple into the pitching motion at the low angles of attack and disturbance levels investigated herein after the introduction of control-surface damping.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55C22
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  • 92
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    Longitudinal Stability and Control Characteristics as Determined by the Rocket-model Technique for an Inline, Cruciform, Canard Missile Configuration with a Low-aspect-ratio Wing Having Trailing-edge Flap Controls for a Mach Number Range of 0.7 to 1. (1955)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-ratio wing equipped with flap-type controls were flight tested in order to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach number from 0.7 to 1.8. Nonlinear lift and moment curves were noted for the angle - of-attack range of this test (0 deg to 8 deg). The aerodynamic-center location for angles of attack near 50 remained nearly constant for supersonic speeds at 13.5 percent of the mean aerodynamic chord; whereas for angles of attack near 0 deg, there was a rapid forward movement of the aerodynamic center as the Mach number increased. At a control deflection of 0 deg, the missile's response to the longitudinal control was in an essentially fixed space plane which was not coincident with the pitch plane as a result of the missile rolling. As a consequence, stability characteristics were determined from the resultant of pitch and yaw motions. The damping-in-pitch derivatives for the two angle -of-attack ranges of the test are in close agreement and varied only slightly with Mach number. The horn-balanced trailing-edge flap was effective in producing angle of attack over the Mach number range.
    Keywords: Aerodynamics
    Type: NACA-RM-L54B12
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  • 93
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    Effects of Body Shape on the Drag of a 45 degree Sweptback-Wing-Body Configuration at Mach Numbers from 0.90 to 1.43 (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation was made of the effects of body shape on the drag of a 45 deg sweptback-wing-body combination at Mach numbers from 0.90 to 1.43. Both the expansion and compression fields induced by body indentation were swept back as the stream Mach number increased from 0.94. The line of zero pressure change was generally tangent to the Mach lines associated with the local velocities over the wing and body. The strength of the induced pressure fields over the wing were attenuated with spanwise distance and the major effects were limited to the inboard 60 percent of the wing semispan. Asymmetrical body indentation tended to increase the lift on the forward portion of the wing and reduce the lift on the rearward portion. This redistribution of lift had a favorable effect on the wave drag due to lift. Symmetrical body indentation reduced the drag loading near the wing-body juncture at all Mach numbers. The reduction in drag loading increased in spanwise extent as the Mach number increased and the line of zero induced pressure became more nearly aligned with the line of maximum wing thickness. Calculations of the wave drag due to thickness, the wave drag due to lift, and the vortex drag of the basic and symmetrical M = 1.2 body and wing combinations at an angle of attack of 0 deg predicted the effects of indentation within 11 percent of the wing-basic-body drag throughout the Mach number range from 1.0 to 1.43. Calculations of the wave drag due to thickness, the wave drag due to lift, and the vortex drag for the basic, symmetrical M = 1.2, and asymmetrical M = 1.4 body and wing combinations predicted the total pressure drag to within 8 percent of the experimental value at M = 1.43.
    Keywords: Aerodynamics
    Type: NASA-MEMO-10-23-58L
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  • 94
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    Inclined Bodies of Various Cross Sections at Supersonic Speeds (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: To aid in assessing effects of cross-sectional shape on body aerodynamics, the forces and moments have been measured for bodies with circular, elliptic, square, and triangular cross sections at Mach numbers 1.98 and 3.88. Results for bodies with noncircular cross sections have been compared with results for bodies of revolution having the same axial distribution of cross-sectional area (and, thus, the same equivalent fineness ratio). Comparisons have been made for bodies of fineness ratios 6 and 10 at angles of attack from 0 deg to about 20 deg and for Reynolds numbers, based on body length, of 4.0 x 10(exp 6) and 6.7 x 10(exp 6). The results of this investigation show that distinct aerodynamic advantages can be obtained by using bodies with noncircular cross sections. At certain angles of bank, bodies with elliptic, square, and triangular cross sections develop considerably greater lift and lift-drag ratios than equivalent bodies of revolution. For bodies with elliptic cross sections, lift and pitching-moment coefficients can be correlated with corresponding coefficients for equivalent circular bodies. It has been found that the ratios of lift and pitching-moment coefficients for an elliptic body to those for an equivalent circular body are practically constant with change in both angle of attack and Mach number. These lift and moment ratios are given very accurately by slender-body theory. As a result of this agreement, the method of NACA Rep. 1048 for computing forces and moments for bodies of revolution has been simply extended to bodies with elliptic cross sections. For the cases considered (elliptic bodies of fineness ratios 6 and 10 having cross-sectional axis ratios of 1.5 and 2), agreement of theory with experiment is very good. As a supplement to the force and moment results, visual studies of the flow over bodies have been made by use of the vapor-screen, sublimation, and white-lead techniques. Photographs from these studies are included in the report.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-MEMO-10-3-58A
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  • 95
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    Experimental Wind-Tunnel Investigation of the Transonic Damping-in-Pitch Characteristics of Two Wing-Body Combinations (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The results of an experimental wind-tunnel investigation of the damping in pitch of two wing-body combinations are presented. The tests were conducted in the Ames 14-foot transonic wind tunnel over a Mach number range from 0.60 to 1.18. Reynolds numbers varied from 2.3 million to 5.5 million. One model with a triangular wing of aspect ratio 2 having NACA 0003-63 sections was oscillated at an amplitude of 1.5 and a frequency of 17 cycles per second. The second model with a straight, tapered wing of aspect ratio 3 having 3-percent biconvex circular-arc sections was oscillated at an amplitude of 1.0 deg and a frequency of 21 cycles per second. The tests were made with the models at a mean angle of attack of 0 deg. The models were oscillated with a dynamic balance that was actuated by an electrohydraulic servo valve. The results of this investigation indicate the usefulness of this new apparatus. The experimental results of a previous damping-in-pitch investigation conducted in the Ames 6- by 6-foot supersonic wind tunnel at Mach numbers from 1.2 to 1.7 are included along with the theoretical results for this Mach number range. In the region of Mach numbers available for comparison, good agreement is shown to exist between the data obtained in the two facilities, except for some inconsistency in the slopes of the curves at M = 1.2 for the triangular wing. The results of this investigation clearly show that for the models tested the maximum values of the damping in pitch occur at Mach numbers very close to 1.0, and that abrupt changes in the pitch damping are encountered near sonic velocity.
    Keywords: Aerodynamics
    Type: NASA-MEMO-11-30-58A
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  • 96
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    Heat Transfer in the Turbulent Incompressible Boundary Layer (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Superposition techniques are used to calculate the rate of heat transfer from a flat plate to a turbulent incompressible boundary layer for several cases of variable surface temperature. The predictions of a number of these calculations are compared with experimental heat- transfer rates, and good agreement is obtained. A simple computing procedure for determining the heat-transfer rates from surfaces with arbitrary wall-temperature distributions is presented and illustrated by two examples. The inverse problem of determining the temperature distribution from an arbitrarily prescribed heat flux is also treated, both experimentally and analytically.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: MEMO-12-3-58W , CF-1
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  • 97
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    An Investigation of the Drag Characteristics of a Tailless Delta-Wing Airplane in Flight, Including Comparison with Wind-Tunnel Data (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A series of flight tests were conducted to determine the lift and drag characteristics of an F4D-1 airplane over a Mach number range of 0.80 to 1.10 at an altitude of 40,000 feet. Apparently satisfactory agreement was obtained between the flight data and results from wind-tunnel tests of an 0.055-scale model of the airplane. Further tests show the apparent agreement was a consequence of the altitude at which the first tests were made.
    Keywords: Aerodynamics
    Type: NASA-MEMO-10-8-58A
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  • 98
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    Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration with a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8 (1955)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-ratio wing equipped with flap-type controls were flight tested in order to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach number from 0.7 to 1.8. Nonlinear lift and moment curves were noted for the angle-of-attack range of this test (0 deg to 8 deg ). The aerodynamic-center location for angles of attack near 5 deg remained nearly constant for supersonic speeds at 13.5 percent of the mean aerodynamic chord; whereas for angles of attack near O deg, there was a rapid forward movement of the aerodynamic center as the Mach number increased. At a control deflection of O deg, the missile's response to the longitudinal control was in an essentially fixed space plane which was not coincident with the pitch plane as a result of the missile rolling. As a consequence, stability characteristics were determined from the resultant of pitch and yaw motions. The damping-in-pitch derivatives for the two angle-of-attack ranges of the test are in close agreement and varied only slightly with Mach number. The horn-balanced trailing-edge flap was effective in producing angle of attack over the Mach number range.
    Keywords: Aerodynamics
    Type: NACA-RM-L54B12
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  • 99
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    Aerodynamic characteristics at mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Resilts have been obtained from an investigation in the Langley Unitary Plan wind tunnel at Mach numbers from 2.5 to 3.5 of a canard-type configuration designed for supersonic cruise flight. Tests extended over an angle-of-attack range from about -4 deg to 11 deg and an angle-of-sideslip range from -4 deg to 6 deg. For the present tests, the results indicate that forebody deflection was an efficient means of providing a sizable positive pitching-moment shift with little or no increase in drag. The test configuration had a trimmed lift-drag ratio of approximately 6.0 at Mach numbers near 3.0 and at a Reynolds number of 2.52 X 10(exp 6). The configuration was both longitudinally and directionally stable. The lift-drag ratios are believed to be somewhat low in as much as the models used for the present tests had large-grain size transition strips fixed to the various surfaces and these strips added wave drag. Also, the model boundary-layer diverter is oversized with respect to a full-scale configuration and therefore contributes additional drag.
    Keywords: Aerodynamics
    Type: NACA-RM-L58G16
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  • 100
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    Investigation of the Static Lateral Stability and Aileron Characteristics of a 0.067-Scale Model of the Bell X-2 Airplane at Mach Numbers of 2.29, 2.78, 3.22, and 3.71 (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Tests were performed in the high. Mach number test section of the Langley Unitary Plan wind tunnel to determine the static lateral stability. and aileron characteristics of a 0.067-scale model of the Bell X-2 airplane at Mach numbers of 2.29, 2. 78, 3.22, and. 3.71. The results of this investigation indicated that the directional stability of the model was low with directional instability occurring at Mach numbers higher than 3.1 and. angles of attack higher than about 5.0 deg (equivalent lift coefficient of about 0.18). The yaw due to aileron deflection was adverse and, with 10 deg of differential aileron deflection, large enough to overbalance the available directional restoring moment at all angles of attack higher than about 5.0 deg (equivalent lift coefficient of about 0.21) and Mach numbers higher than 2. 5. The model also had positive effective dihedral for all test attitudes and. Mach numbers. A combination of the lateral-stability parameters with the aileron characteristics to form a lateral-stability criterion for a maneuver using ailerons alone indicated that the model has characteristics which would. give unstable aperiodic behavior (divergence) over a large part of the test Mach number and angle-of-attack range.
    Keywords: Aerodynamics
    Type: NACA-RM-L57J28a
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