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  • Other Sources  (322)
  • 1980-1984
  • 1945-1949
  • 1930-1934  (322)
  • 1925-1929
  • 1933  (160)
  • 1932  (162)
  • 1
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    Tilting due to glacial melting (1933)
    In:  The Journal of Geology, Milano, Gustav Fischer, vol. 41, no. 3, pp. 449-467, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Über Erdbeben mit Herdtiefen von mehreren hundert Kilometern (1933)
    In:  Geologische Rundschau, Milano, Gustav Fischer, vol. 24, no. 3, pp. 227-239, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Seismology ; Hypocentral depth ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Is present tilting in North America due to glacial melting (1932)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 67-68, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Experiments testing seismographic methods for determining crustal structure (1932)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 65-66, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Re suggestion by Dr. Harold Jeffreys regarding P(bar) and Pg (1933)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 40, no. 3, pp. 97-98, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Seismology ; P-waves ; CRUST
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Is present tilting in North America due to glacial melting ? (1933)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 44, no. 3, pp. 152-153, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Advantages of using geocentric latitude in calculating distances (1933)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 40, no. 3, pp. 380-389, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: mathematics ; geometry ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Travel time curves at small distances and wave velocities in Southern California (1932)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 35, no. 3, pp. 6-45, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Travel time ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Experiments testing seismographic methods for determining crustal structure (1933)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 44, no. 3, pp. 170-171, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; Velocity depth profile
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Berichtigungen und Ergänzungen zu Band 4 (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 4: Erdbeben (finished), 12+ 1202 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1186-1190, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Seismology ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Der Aufbau der Atmosphäre (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 9: Physik der Atmosphäre 2 (only 1., 2., and 3. part), 8 + 698 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1-88, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Meteorology
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Mit welcher Genauigkeit läßt sich die Schallgeschwindigkeit in der Stratosphäre finden? (1932)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 35, no. 3, pp. 46-50, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Velocity analysis ; Meteorology ; Acoustics
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Structure of the earth's crust derived from seismograms (1932)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 43, no. 3, pp. 236-237, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: CRUST ; Seismology ; Seismics (controlled source seismology)
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    The earthquake in Santa Monica Bay, California, on August 30, 1930 (1932)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 138-154, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismology ; Earthquake ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Experiments testing seismographic methods for determining crustal structure (1932)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 185-246, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Erde (physikalische Beschaffenheit) (1933)
    Gustav Fischer
    In:  Professional Paper, Handwörterbuch der Naturwissenschaften Bd. 3, Jena, Gustav Fischer, vol. 3, no. VIIa, pp. 762-774, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1933
    Keywords: Handbook of geophysics ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    Dürrezahlen, ein Versuch, die Auswirkungen von Dürreperioden klimastatistisch zu erfassen (1933)
    In:  Fortschritte der Landwirtschaft, 8: 313-316
    Details
    Publication Date: 1933
    Description: Beschreibung der Häufigkeitsverteilung von Trockenperioden durch Belegung und Gewichtung von niederschlagsfreien Tagen im Mittel von Dekaden KATASTER-BESCHREIBUNG: Betrachtung einzelner Dekaden, Vergleich der Häufigkeitsverteilung der Dürrezahlen, Schlussfolgerungen für die Gefährdung durch Dürre für die Landwirtschaft KATASTER-DETAIL: Delta Nied- (Dez-März), Hervortreten des Winters als Dürrezeit im Raum Wien
    Keywords: Utrecht, Wien ; 1851-1910, 1881-1920 ; Landwirtschaft ; Niederschlag ; Trockenheit
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    BIBLIOGRAPHY INKA BB
  • 18
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    Der Nonnenraupenfraß achtzehnhundertneunundachtzig / einundneunzig und der Wirbelsturm vom 14. Juli 1894 im Ebersbergerforst (1933)
    Details
    Publication Date: 1933
    Description: brauchbare Anekdote für Zwischenbericht INKA-BB KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
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  • 19
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    Hat das Wetter Einfluß auf den Eintritt des Todes? (1933)
    In:  Virchows Archiv für Pathologische Anatomie und Physiologie und für Klinische Medizin, v291 n1-2, 237-259
    Details
    Publication Date: 1933
    Description: statistische Bearbeitung von über 16.000 Berliner Sektionsfällen, Vergleich der täglichen Sterbeziffer mit der Wetterlage KATASTER-BESCHREIBUNG: Zunahme der Mortalität an Kaltfront- und Warmfronttagen KATASTER-DETAIL:
    Keywords: Berlin ; 1926-1928 ; Umweltmedizin ; Witterung
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  • 20
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    Der Einfluß klimatischer Faktoren auf die Höhe des Pflanzenertrages (1933)
    In:  Vortrag, Schr. Königsberg. gel. Ges., Naturwiss. Kl., 10 H.6) Max Niemeyer, Halle a. S.:16
    Details
    Publication Date: 1933
    Description: Untersuchungen über den Einfluss klimatischer Wachstumsfaktoren auf den Ertrag KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenschein) auf den Ertrag KATASTER-DETAIL: Delta Luftdruck +, dann Erträge +; Delta O2-Gehalt (Luft) = 15 %, dann Ertrag = max; Delta CO2-Gehalt (Luft) = 0.03 %, dann Ertrag = max; Delta Lichtintensität - und Delta CO2-Gehalt +, dann Ertrag +; Delta T Boden, Vegetationszeit) + : Tmit 〉 5 °C, dann Ertrag; Delta Nied +, dann Ertrag +;
    Keywords: Königsberg, Preußen ; 1931-1932 ; Boden ; Ertrag ; Niederschlag ; Temperatur ; Wind ; Witterung ; Sonnenscheindauer
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  • 21
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    Der Maikäfer in Württemberg (1933)
    In:  Monographie; Reihe: Arbeit aus der Landesanstalt für Pflanzenschutz Hohenheim; Ulmer Verlag, Stuttgart; 140p.
    Details
    Publication Date: 1933
    Description: Das Auftreten des Maikäfers in Württemberg, sowie seine räumlich differenzierte Ausprägung wird in Abhängigkeit klimatischer und nicht-klimatischer Faktoren betrachtet. Eine detaillierte Karte hierzu ist enthalten. Entwicklungsdauer und Folgenzahl des Maikäfers werden als Funktion der Temperatur graphisch dargestellt; außer den Reinformen des 3- und 4-jährigen Zyklus werden noch Mischformen und ihr temperaturbedingt unterschiedliches Auftreten in Württemberg beleuchtet. KATASTER-BESCHREIBUNG: Entwicklungsgeschwindigkeit hängt von der Temp. ab (Bsp.: durch Temp.erhöhung im Warmhaus wurde die Fraßzeit um 4 Monate verlängert und folglich die Verpuppung um 5-6 Monate vorverlegt =〉 die Käfer verließen den Boden schon 1 Jahr früher als durch ihren Entwicklungszyklus normal gewesen wäre KATASTER-DETAIL:
    Keywords: Württemberg ; 1836-1928 ; Forst ; Pflanzenschädling
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  • 22
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    Beziehungen der Sommerwitterung im nördlichen Alpenvorland mit dem Vorwetter. III. Sommerwitterung und Ernteerträgnis (1933)
    In:  Meteorologische Zeitschrift 8:300-306.
    Details
    Publication Date: 1933
    Description: Korrelation zwischen Junitemperaturen und Hafererträgen Regressionsgleichung (Temperaturzunahme bedingt Ertragsrückgang) KATASTER-BESCHREIBUNG: Einfluss der Junitemperatur auf die Haferernte KATASTER-DETAIL: Delta T (Juni) +, dann Erträge --; Änderungen um +1°C, dann Verminderung der Erträge um ~2,1 Zentner; Änderungen um +5°C, dann Verminderung der Erträge um 10 Zentner pro 1 ha
    Keywords: Niederbayern und Oberösterreich ; 1885-1925 ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung
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  • 23
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    Witterung und Insekten in der Gegend von Rostock 1932 (1933)
    In:  Anzeig. Schädlingskunde 9; p.29-34
    Details
    Publication Date: 1933
    Description: Der Autor beschreibt Beobachtungen über verschiedene schädigende und nicht schädigende Insekten im Acker- und Obstbau, sowie der Forstwirtschaft und versucht ihre Ursachen im Wetter des Jahres 1932 zu finden. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Mecklenburg-Vorpommern ; 1932 ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung
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  • 24
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    Witterung und Insekten (1933)
    In:  Anzeig. Schädlingskunde 9; p.109-112
    Details
    Publication Date: 1933
    Description: Der Autor diskutiert im Bezug auf einen Artikel von Friederichs in der selben Zeitschrift den Zusammenhang zwischen Wetter bzw. Witterung und dem Auftreten von Insekten insbesondere Blattläusen und vergleicht diese mit eigenen Beobachtungen. Folgende Erkenntnisse erschließen sich aus seinen eigenen Beobachtungen: Im Frühjahr entwickeln sich Pflanzen auch wenn es kühl ist gut, Insekten dagegen weniger, wenn genug Licht zur Verfügung steht. Rolle der Feuchtigkeit (nicht zwangsweise als Niederschlag) wird hervorgehoben. Beständige Witterung ist für die Individuenzahl einer Insektenpopulation förderlich KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bergedorf ; 1932
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  • 25
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    Handbuch der Geophysik, Volume 7: Physik der Hydrosphäre (only 1. part), 5 + 252 S. (1933)
    Bornträger
    In:  Berlin, Bornträger, vol. 12, 189 S., no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1933
    Keywords: Handbook of geophysics ; oceanography
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    BIBLIOGRAPHY SEISMOLOGY
  • 26
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    Die Schallausbreitung in der Atmosphäre (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 9: Physik der Atmosphäre 2 (only 1., 2., and 3. part), 8 + 698 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 89-145, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Meteorology ; Wave propagation ; Acoustics
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    BIBLIOGRAPHY SEISMOLOGY
  • 27
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    The command system malfunction of the telstar satellite (1932)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Command system malfunction of telstar satellite due to transistor surface damage in redundant command decoder
    Keywords: COMPUTERS
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    NASA TECHNICAL REPORTS
  • 28
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    Test of NACA 21 Airfoil (Modified NACA M-6) Including Characteristics at Positive and Negative Angles of Attack (1932)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance; Research and Support Facilities (Air); Aerodynamics
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    NASA TECHNICAL REPORTS
  • 29
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    Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-477
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  • 30
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    Wind-tunnel tests on model wing with Fowler flap and specially developed leading-edge slot (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made in the NACA 7 by 10 foot wind tunnel to find the increase in maximum lift coefficient which could be obtained by providing a model wing with both a Fowler trailing-edge extension flap and a Handley Page type leading-edge slot. A conventional Handley page slot proportioned to operate on the plain wing without a flap gave but a slight increase with the flap; so a special form of slot was developed to work more effectively with the flap. With the best combined arrangement the maximum lift coefficient based on the original area was increased from 3.17, for the Fowler wing, to 3.62. The minimum drag coefficient with both devices retracted was increased in approximately the same proportion. Tests were also made with the special-type slot on the plain wing without the flap. The special slot, used either with or without the Fowler flap, gave definitely higher values of the maximum lift coefficient than the slots of conventional form, with an increase of the same order in the minimum drag coefficient.
    Type: NACA-TN-459
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  • 31
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    The German Investigation of the Accident at Meopham (England) (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is a recounting of the German investigation of the crash of a commercial Junkers F 13 ge in England. The English report is examined and compared with the German interpretation of the accident.
    Type: NACA-TM-669
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  • 32
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    Development of tailless and all-wing gliders and airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tailless airplanes are characterized by having all their control surfaces, especially the elevator, incorporated in the wings. This paper provides a discussion of the history of their development and current state of development.
    Type: NACA-TM-666
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  • 33
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    Twelfth Rhon soaring contest, 1931 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The crew of the "Fafnir" was given an excellent opportunity for collecting first-hand data as to the usefulness of gliders in the Alps. It is necessary to recount the remarkable glider achievements ahead of the Rhon Soaring Contest, in order to understand the tension and expectation with which the Rhon contest was anticipated.
    Type: NACA-TM-671
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  • 34
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    Towing tests of models as an aid in the design of seaplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report concerns the making and evaluation of a towing test of a seaplane float system. Some of the topics considered are: 1) the influence of the wing cell and power plant on the take-off performance; 2) the determination of the resistance curve for the take-off free to trim; 3) the resistance curves with elevator control (at fixed trims); 4) take-off time and take-off run.
    Type: NACA-TM-676 , Gesellschaft der Freunde und Forderer der Hamburgischen Schiffbau-Versuchsanstalt (9th : June 11, 1930)
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  • 35
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    Airplane stability in taxying (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
    Type: NACA-TM-682
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  • 36
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    Speed and pressure recording in three-dimensional flow (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Van der Megge Zijnen's spherical Pitot tube with its 5 test holes insures a simultaneous record of static pressure and magnitude and direction of velocity in three-dimensional flow. The report treats the method as well as the range of application of this Pitot in the light of modern knowledge on flow around spheres.
    Type: NACA-TM-688
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  • 37
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    The Problem of Tire Sizes for Airplane Wheels (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: On the basis of experiments and theoretical considerations a proposal is made for a standard tire series for airplane wheels, without regard to existing standards.
    Type: NACA-TM-689
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  • 38
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    Development of the Rules Governing the Strength of Airplanes. Part I : German Loading Conditions up to 1926 (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Load factors and loading conditions are presented for German aircraft. Loading conditions under various stress factors are presented along with a breakdown of individual aircraft components such as landing gear, wings, etc.
    Type: NACA-TM-716
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  • 39
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    Guide Vanes for Deflecting Fluid Currents with Small Loss of Energy (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The transverse momentum of the deflected air stream to be absorbed is divided between the intermediate and outside walls, so that the pressure increase on each wall is much smaller and the danger of separation is diminished. The formation of secondary vortices is also diminished. By taking as the basis profiles with high c(sub a), such as have proved practically favorable, it is not possible to find a satisfactory form of grid simply on the assumption that the flow is potential. The requirements called for the most uniform possible velocity distribution behind the bend and the smallest possible losses.
    Type: NACA-TM-722
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  • 40
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    Attaining a steady air stream in wind tunnels (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Many experimental arrangements of varying kind involve the problems of assuring a large, steady air stream both as to volume and to time. For this reason a separate discussion of the methods by which this is achieved should prove of particular interest. Motors and blades receive special attention and a review of existent wind tunnels is also provided.
    Type: NACA-TM-726
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  • 41
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    Development of the rules governing the strength of airplanes. Part III : loading conditions in France, Italy, Holland, and Russia - aims at standardization (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The historical development of the rules for structural strength of aircraft in the leading countries is traced from the beginning of flight to date. The term "factor of safety" is critically analyzed; its replacement by probability considerations has been considered desirable.
    Type: NACA-TM-718
    Format: application/pdf
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  • 42
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    Development of Air-cooled Engines with Blower Cooling (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: With the aid of a heating device, the heat transfer to cylinders with conical fins of various forms is determined both for shrouded and exposed cylinders. Simultaneously the pressure drop for overcoming the resistance to the motion of air between the fins of the enclosed cylinder is measured. Thus the relations between the heat transfer and the energy required for cooling are discovered. The investigations show that the heat transfer in a conducted air flow is much greater than in a free current and that further improvement, as compared with free exposure, is possible through narrower spaces between the fins.
    Type: NACA-TM-725
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  • 43
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    Trend of airplane flight characteristics (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the development of airplane characteristics since the war and indicates the direction development should take in the immediate future. Some of the major topics include: the behavior of an airplane about its lateral, vertical, and longitudinal axes. Behavior at large angles of attack and landing characteristics are also included.
    Type: NACA-TM-731 , Deutsche Versuchsanstalt fur Luftfahrt ( 1932 : Berlin)
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  • 44
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    Combustion Velocity of Benzine-Benzol-Air Mixtures in High-Speed Internal-Combustion Engines (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present paper describes a device whereby rapid flame movement within an internal-combustion engine cylinder may be recorded and determined. By the aid of a simple cylindrical contact and an oscillograph the rate of combustion within the cylinder of an airplane engine during its normal operation may be measured for gas intake velocities of from 30 to 35 m/s and for velocities within the cylinder of from 20 to 25 m/s. With it the influence of mixture ratios, of turbulence, of compression ratio and kind of fuel on combustion velocity may be determined. Besides the determination of the influence of the above factors on combustion velocity, the degree of turbulence may also be determined. As a unit of reference in estimating the degree of turbulence, the intake velocity of the charge is chosen.
    Type: NACA-TM-668
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  • 45
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    Vertical descent of the autogiro (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this report is to show that only part of the system of rotating blades really is in the "windmill decelerating attitude" when the profile drag is sufficiently low. This particular part receives more torque from the air loads than can be absorbed by the profile drag. As a result thereof the rotating autogiro blade, when its torque is zero, is in part a propeller which functions in the "annular vortex attitude."
    Type: NACA-TM-673
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  • 46
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    Stresses developed in seaplanes while taking off and landing (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the case of seaplanes, the lack of elastic shock absorbers, the presence of which might be quite dangerous, especially in taking off, makes it necessary to give some consideration to the phenomenon of landing. Special consideration must be given the process of taking off, since even moderately rough water may develop rather large stresses. The purpose of this communication is to show what has been accomplished in Italy and other countries and to draw a few useful conclusions.
    Type: NACA-TM-677 , Societa Italiana per il Progresso delle Scienze (20th : 1931 : Milan, Italy)
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  • 47
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    An Airfoil Spanning an Open Jet (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Proceeding from the fundamental problem on the mutual relation of a wing and free boundaries the distribution of the circulation is determined for an airfoil spanning an open jet of rectangular section at different aspect ratios, and then for an open jet of circular section. The solution is obtained by means of a Fourier series and computations have been performed for different values of the variables. The second part describes the experiments performed for the purpose of proving the theory. The results confirm the theory. In conclusion it defines the induced drag of a wing extending across an open jet and compares it with the drag of a monoplane having a span equal to the jet width at equal total lift.
    Type: NACA-TM-723
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  • 48
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    The flight of an autogiro at high speed (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a method for computing the flight performance of an autogiro at high speed, the velocity component along the blades being accounted for by calculation of the profile drag and the equation for zero torque.
    Type: NACA-TM-729
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  • 49
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    Wind-tunnel research comparing lateral control devices, particularly at high angles of attack III : ordinary ailerons rigged up 10 degrees when neutral (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind-tunnel tests made on three model wings having different sizes of ordinary ailerons rigged up 10 degrees when neutral, the same models having previously been tested with the ailerons rigged even with the wings in the usual manner. One of the wings had ailerons of medium size, 25 per cent of the wing chord by 40 per cent of the semispan, one had long, narrow ailerons, and one had short, wide ones. These tests are part of a general investigation on lateral control devices, with particular reference to the control at high angles of attack, in which all the devices are being subjected to the same series of tests in the 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics. Force tests of the usual type, free-autorotation tests, and forced-rotation tests were made showing the effect of the ailerons on the general performance of the wing, on the lateral controllability, and on the lateral stability.
    Type: NACA-TR-423
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  • 50
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    Wind-tunnel research comparing lateral control devices, particularly at high angles of attack I : ordinary ailerons on rectangular wings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the first in a series in which it is intended to compare the relative merits of all ordinary and some special forms of ailerons and other lateral control devices in regard to their effect on lateral controllability, lateral stability, and airplane performance. The comparisons are based on wind-tunnel test data, all the control devices being fitted to model wings having the same span, area, and airfoil section, and being subjected to the same series of force and rotation tests. The results are given for five different aileron movements: one with equal up-and-down deflection, one with average and one with extreme differential motion, one with upward deflection only, and one with the ailerons arranged to float with respect to the wing.
    Type: NACA-TR-419
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  • 51
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    Theory of wing sections of arbitrary shape (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a solution of the problem of the theoretical flow of a frictionless incompressible fluid past airfoils of arbitrary forms. The velocity of the 2-dimensional flow is explicitly expressed for any point of the surface, and for any orientation, by an exact expression containing a number of parameters which are functions of the form only and which may be evaluated by convenient graphical methods. The method is particularly simple and convenient for bodies of streamline forms. The results have been applied to typical airfoils and compared with experimental data.
    Type: NACA-TR-411
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  • 52
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    The Aerodynamic Characteristics of a Slotted Clark Y Wing as Affected by the Auxiliary Airfoil Position (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose.
    Type: NACA-TR-400
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  • 53
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    Flame Movement and Pressure Development in an Engine Cylinder (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation describes a visual method for making stroboscopic observations, through a large number of small windows, of the spread of flame throughout the combustion chamber of a gasoline engine. Data, secured by this method on a small engine burning gaseous fuels, are given to show the effects of mixture ratio, spark advance, engine speed, charge density, degree of dilution, compression ratio, and fuel composition on flame movement in the cylinder. Partial indicator diagrams showing pressure development during the combustion period are included. Although present knowledge is not sufficient to permit qualitative evaluation of the separate effects on flame movement of chemical reaction velocity, thermal expansion of burned gases, resonance, turbulence, and piston movement, the qualitative influence of certain of these factors on some of the diagrams is indicated.
    Type: NACA-TR-399
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  • 54
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    Investigation of Damping Liquids for Aircraft Instruments : II (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented on the kinematic viscosity, in the temperature range -50 degrees to +30 degrees C. of pure liquids and of solutions of animal oils, vegetable oils, mineral oils, glycerine, and ethylene glycol in various low freezing point solvents. It is shown that the thermal coefficient of kinematic viscosity as a function of the kinematic viscosity of the solutions of glycerine and ethylene glycol in alcohols is practically independent of the temperature and the chemical composition of the individual liquids. This is similarly true for the mineral oil group and, for a limited temperature interval, for the pure animal and vegetable oils. The efficiency of naphthol, hydroquinone, and diphenylamine to inhibit the change of viscosity of poppyseed and linseed oils was also investigated.
    Type: NACA-TR-398
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  • 55
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    Full-Scale Tests of Metal Propellers at High Tip Speeds (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests of 10 full-scale metal propellers of several thickness ratios at various tip speeds up to 1,350 feet per second. The results indicate no loss of efficiency up to tip speeds of approximately 1,000 feet per second. Above this tip speed the loss is at a rate of about 10 per cent per 100 feet per second increase relative to the efficiency at the lower speeds for propellers of pitch diameter ratios 0.3 to 0.4. Propellers having sections of small thickness ratio can be run at slightly higher speeds than thick ones before beginning to lose efficiency.
    Type: NACA-TR-375
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  • 56
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    Present status of aircraft instruments (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a brief description of the present state of development and of the performance characteristics of instruments included in the following group: speed instruments, altitude instruments, navigation instruments, power-plant instruments, oxygen instruments, instruments for aerial photography, fog-flying instruments, general problems, summary of instrument and research problems. The items considered under performance include sensitivity, scale errors, effects of temperature and pressure, effects of acceleration and vibration, time lag, damping, leaks, elastic defects, and friction.
    Type: NACA-TR-371
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  • 57
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    A new chart for estimating the absolute ceiling of an airplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the derivation of a chart for estimating the absolute ceiling of an airplane. This chart may be used in conjunction with the usual curves of power required and power available as an accurate substitute for extended calculation, or it may be used in the estimation of absolute ceiling when power curves are not available.
    Type: NACA-TR-368
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  • 58
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    Maneuverability Investigation of the F6C-3 Airplane with Special Flight Instruments (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made for the purpose of obtaining information on the maneuverability of the F6C-3 airplane. It is the first of a series of similar investigations to be conducted on a number of military airplanes for the purpose of comparing the abilities of these airplanes to maneuver, and also to establish a fund of quantitative data which may be used in formulating standards of comparison for rating the maneuverability of any airplane. A large part of this initial investigation was necessarily devoted to the development and trial of methods suitable for use in subsequent investigations of this nature. Air speed, angular velocity, linear acceleration, and position of the control surfaces were measured by instruments in the airplane during loops, push-downs, pull-outs from dives, pull-ups from level flight, barrel rolls, and spins. The coordinates of flight paths were deduced from the data whenever possible, and were checked in some cases by the use of a camera obscura. The results are given in curves showing the variation of the measured quantities with respect to time, and maximum values are tabulated.
    Type: NACA-TR-369
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  • 59
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    Annual report of the National Advisory Committee for Aeronautics (17th).administrative report including Technical Report nos. 365 to 400 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Type: NACA-AR-17
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  • 60
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    Measurements of Flow in the Boundary Layer of a 1/40-Scale Model of the U. S. Airship "Akron." (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of measurements of flow in the boundary layer of a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4) made with the object of determining the boundary-layer thickness, the point of transition from laminar to the turbulent flow, and the velocity distribution in the boundary layer.
    Type: NACA-TR-430
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  • 61
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    Rates of fuel discharge as affected by the design of fuel-injection systems for internal-combustion engines (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Using the method of weighing fuel collected in a receiver during a definite interval of the injection period, rates of discharge were determined, and the effects noted, when various changes were made in a fuel-injection system. The injection system consisted primarily of a by-pass controlled fuel pump and an automatic injection valve. The variables of the system studied were the pump speed, pump-throttle setting, discharge-orifice diameter, injection-valve opening and closing pressures, and injection-tube length and diameter.
    Type: NACA-TR-433
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  • 62
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    Wind-tunnel tests of a Clark Y wing with a narrow auxiliary airfoil in different positions (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests were made on a combination of a Clark Y wing and a narrow auxiliary airfoil to find the best location of the auxiliary airfoil with respect to the main wing. The auxiliary was a highly cambered airfoil of medium thickness having a chord 14.5 per cent that of the main wing. It was tested in 141 different positions ahead of, above, and behind the nose portion of the main wing, the range of the test points being extended until the best aerodynamic conditions were covered. A range of positions was found in which the combination of main wing and auxiliary gave substantially greater aerodynamic efficiency and higher maximum lift coefficients (based on total area) than the main Clark Y wing alone. In the optimum position tested, considering both the maximum lift and the speed-range ratio, the combination of main wing and auxiliary gave an increase in the maximum lift coefficient of 32 per cent together with an increase in the ratio of 21 per cent of the respective values for the main Clark Y wing alone.
    Type: NACA-TR-428
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  • 63
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    The effect of multiple fixed slots and a trailing-edge flap on the lift and drag of a Clark Y airfoil (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Lift and drag tests were made on a Clark Y wing equipped with four fixed slots and a trailing-edge flap in the 5-foot vertical wind tunnel of the National Advisory Committee for Aeronautics. All possible combinations of the four slots were tested with the flap neutral and the most promising combinations were tested with the flap down 45 degrees. Considering both the maximum lift coefficient and the speed-range ratio with the flap neutral no appreciable improvement was found with the use of more than the single leading-edge slot. With the flap down 45 degrees a maximum lift coefficient of 2.60 was obtained but the particular slot combination used had a rather large minimum drag coefficient with the flap neutral. With the flap down 45 degrees the optimum combination, considering both the maximum lift coefficient and the speed-range ratio, was obtained with only the two rearmost slots in use. For this arrangement the maximum lift coefficient was 2.44.
    Type: NACA-TR-427
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  • 64
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    The 7 by 10 Foot Wind Tunnel of the National Advisory Committee for Aeronautics (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
    Type: NACA-TR-412
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  • 65
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    The Elimination of Fire Hazard Due to Back Fires (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A critical study was made of the operation of a type of back-fire arrester used to reduce the fire hazard of aircraft engines. A flame arrester consisting of a pack or plug of alternate flat and corrugated plates of thin metal was installed in the intake pipe of a gasoline engines; an auxiliary spark plug inserted in the intake manifold permitted the production of artificial back fires at will. It was found possible to design a plug which prevented all back fires from reaching the carburetor.
    Type: NACA-TR-409
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  • 66
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    Drop and Flight Tests on NY-2 Landing Gears Including Measurements of Vertical Velocities at Landing (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to obtain quantitative information on the effectiveness of three landing gears for the NY-2 (consolidated training) airplane. The investigation consisted of static, drop, and flight tests on landing gears of the oleo-rubber-disk and the mercury rubber-chord types, and flight tests only on a landing gear of the conventional split-axle rubber-cord type. The results show that the oleo gear is the most effective of the three landing gears in minimizing impact forces and in dissipating the energy taken.
    Type: NACA-TR-406
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  • 67
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    General formulas and charts for the calculation of airplane performance (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents general formulas for the determination of all major airplane performance characteristics. A rigorous analysis is used, making no assumption regarding the attitude of the airplane at which maximum rate of climb occurs, but finding the attitude at which the excess thrust horsepower is maximum. Equations and charts are developed which show the variation of performance due to a change in any of the customary design parameters. Performance determination by use of the formulas and charts is rapid and explicit. The results obtained by this performance method have been found to give agreement with flight tests that is, in general, equal or superior to results obtained by present commonly used methods.
    Type: NACA-TR-408
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  • 68
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    The drag characteristics of several airships determined by deceleration tests (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of deceleration tests conducted for the purpose of determining the drag characteristics of six airships. The tests were made with airships of various shapes and sizes belonging to the Army, the Navy, and the Goodyear-Zeppelin Corporation. Drag coefficients for the following airships are shown: Army TC-6, TC-10, and TE-2; Navy Los Angeles and ZMC-2; Goodyear Puritan. The coefficients vary from about 0.045 for the small blunt airships to 0.023 for the relatively large slender Los Angeles. This variation may be due to a combination of effects, but the most important of these is probably the effect of length-diameter ratio.
    Type: NACA-TR-397
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  • 69
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    The Effect of Valve Timing Upon the Performance of a Supercharged Engine at Altitude and an Unsupercharged Engine at Sea Level (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to determine the comparative effects of valve timing on the performance of an unsupercharged engine at sea level and a supercharged engine at altitude. The tests were conducted on the NACA universal test engine. The timing of the four valve events was varied over a wide range; the engine speeds were varied between 1,050 and 1,500 r.p.m.; the compression ratios were varied between 4.35:1 and 7.35:1. The conditions of exhaust pressure and carburetor pressure of a supercharged engine were simulated for altitudes between 0 and 18,000 feet. The results show that optimum valve timing for a supercharged engine at an altitude of 18,000 feet differs slightly from that for an unsupercharged engine at sea level. A small increase in power is obtained by using the optimum timing for 18,000 feet for altitudes above 5,000 feet. The timing of the intake opening and exhaust closing becomes more critical as the compression ratio is increased.
    Type: NACA-TR-390
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  • 70
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    The Effect of Small Angles of Yaw and Pitch on the Characteristics of Airplane Propellers (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests to determine the effect on the characteristics of a propeller of inclining the propeller axis at small angles to the relative wind. Tests were made of a full-scale propeller and fuselage combination at four angles of yaw (0 degree, +5 degrees, +10 degrees, +15 degrees), and of a model propeller, nacelle, and wing combination of five angles of pitch (-5 degrees, 0 degree, +5 degrees, +10 degrees and +15 degrees). The results of the full-scale tests of a propeller and fuselage, without a wing, show that the effect on the propeller performance is small. Similar results are shown by the model test data except that where the propeller is directly in front of the wing there is an appreciable decrease in effective thrust and propulsive efficiency with increase of angle of pitch.
    Type: NACA-TR-389
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  • 71
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    The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests on a group of eight very thick airfoils having sections of the same thickness as those used near the roots of tapered airfoils. The tests were made to study certain discontinuities in the characteristic curves that have been obtained from previous tests of these airfoils, and to compare the characteristics of the different sections at values of the Reynolds number comparable with those attained in flight. The discontinuities were found to disappear as the Reynolds number was increased. The results obtained from the large-scale airfoil, a symmetrical airfoil having a thickness ratio of 21 per cent, has the best general characteristics.
    Type: NACA-TR-391
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  • 72
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    Comparison of Full-Scale Propellers Having R.A.F.-6 and Clark Y Airfoil Sections (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the propellers with R. A. F.-6 sections gave about the same maximum efficiency as the Clark Y propellers and were more efficient for the conditions of climb and take-off.
    Type: NACA-TR-378
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  • 73
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    Rolling Moments Due to Rolling and Yaw for Four Wing Models in Rotation (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of the rotating wings up to large angles of attack. It was found that at angles of attack above that of maximum lift the rolling moments on the wings due to yaw (or side slip) from 5 degrees to 20 degrees were roughly of the same magnitude as those due to rolling. There was a wide variation in magnitude of the rolling moment due to yaw angle. The rates and ranges of stable autorotation for the monoplane models were considerably increased by yaw, whereas for an unstaggered biplane they were little affected. The immediate cause of the rolling moment due to yaw is apparently the building up of large loads on the forward wing tip and the reduction of loads on the rearward wing tip.
    Type: NACA-TR-379
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  • 74
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    Heinkel HE 70 commercial airplane (German) : a seven-seat cantilever low-wing monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-183
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  • 75
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    The Dewoitine D.500 pursuit airplane (French) : an all-metal cantilever low-wing monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-180
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  • 76
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    The Stieger ST. 4 light airplane (British) : a twin-engine four-seat low-wing cabin monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-164
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  • 77
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    The Farman night bombers 211 and 212 (French) : four-engine high-wing monoplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-165
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  • 78
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    The Shackleton-Murray SM-1 light airplane : a two-place high-wing monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-181
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  • 79
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    Supplement to the Supermarine S.6.B. Racing Seaplane (British) : A Low-Wing Twin-Float Monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-154-Suppl
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  • 80
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    Charts for determining the pitching moment of tapered wings with sweepback and twist (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a convenient method for calculating the pitching-moment characteristics of tapered wings with sweepback and twist. The method is based on the fact that the pitching-moment characteristics of a wing may be specified by giving the value of the pitching moment at zero lift and the location of the axis about which the axis is constant. Data for calculating these characteristics are presented by curves which apply to wings having a linear distribution of twist along the span and which cover a large range of aspect ratios. The curves are given for wings having straight taper and distorted elliptical plan forms. The characteristics of wings of other shapes may be determined by interpolation.
    Type: NACA-TN-483
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  • 81
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    The Effect of Spray Strips on a Model of the P3M-1 Flying Boat Hull (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results of a series of tests made in the N.A.C.A. tank on a one-sixth full-size model of the hull and side floats of the Navy P3M-1 flying boat for the purpose of finding a method of reducing the amount of spray thrown into the propellers of this craft when taking off and landing. The model was tested without spray strips and with five different spray-strip arrangements. The best arrangement was an improvement over the bare hull with no spray strips, but the improvement was not sufficient to be satisfactory with the propellers in the designed position.
    Type: NACA-TN-482
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  • 82
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    The Reduction in Drag of a Forward-sloping Windshield (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper gives results of a short investigation of the drag of a forward-sloping closed-cabin windshield. The drag of the windshield in both the original and a final modified form was determined from tests in the variable-density wind tunnel. The final form of the windshield was arrived at by modifying the original as the result of flow observations in the N.A.C.A. smoke tunnel. The investigation studied the utility of the N.A.C.A. smoke tunnel as applied to reducing the drag of objects for which the full dynamic scale could not be approached in the smoke tunnel, but designers should find the results of the flow observations and drag measurements of value. They show that most of the large drag added by the original windshield is eliminated by the modification of the windshield to the final form.
    Type: NACA-TN-481
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  • 83
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    The Drag of Streamline Wires (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preliminary results are given of drag tests of streamline wires. Full-size wires were tested over a wide range of speeds in the N.A.C.A. high speed tunnel. The results are thus directly applicable to full-scale problems and include any compressibility effects encountered at the higher speeds. The results show how protuberances may be employed on conventional streamline wires to reduce the drag, and also show how the conventional wires compare with others having sections more like strut or symmetrical airfoil sections. Because the new wire sections developed are markedly superior aerodynamically to conventional wires, it is recommended that some of them be tested in service in order to investigate their relative susceptibility to vibration and to fatigue failure.
    Type: NACA-TN-480
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  • 84
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    Engine performance with a hydrogenated safety fuel (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the engine performance obtained with a hydrogenated safety fuel developed to eliminate fire hazard. The tests were made on a single-cylinder universal test engine at compression ratios of 5.0, 5.5, and 6.0. Most of the tests were made with a fuel-injection system, although one set of runs was made with a carburetor when using gasoline to establish comparative performance. The tests show that the b.m.e.p. obtained with safety fuel when using a fuel-injection system is slightly higher than that obtained with gasoline when using a carburetor, although the fuel consumption with safety fuel is higher. When the fuel-injection system is used with each fuel and with normal engine temperatures the b.m.e.p. with safety fuel is from 2 to 4 percent lower than with gasoline and the fuel consumption about 25 to 30 percent higher. However, a few tests at an engine coolant temperature of 250 F have shown a specific fuel consumption approximating that obtained with gasoline with only a slight reduction in power. The idling of the test engine was satisfactory with the safety fuel. Starting was difficult with a cold engine but could be readily accomplished when the jacket water was hot. It is believed that the use of the safety fuel would practically eliminate crash fires.
    Type: NACA-TN-466
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  • 85
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    Some Characteristics of Sprays Obtained from Pintle-type Injection Nozzles (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests made with the pintle-type injection nozzles, one having a pintle angle of 8 degrees, the other a pintle angle of 30 degrees. The fuel was injected into a glass-windowed pressure chamber and the spray photographed by means of the N.A.C.A. spray photography apparatus. Curves are presented that give the penetration of the spray tips when fuel oil is injected by pressures of 1,500 to 4,000 pounds per square inch into air at room temperature and densities of 11 to 18 atmospheres. High-speed spark photographs show the appearance of the sprays in air at a density of 18 atmospheres. The results indicate that the pintle angles have little effect on the size of the spray cone angle, which is about the same as that of sprays from plain round hole orifices. The penetration of the spray from the nozzle with an 8 degree pintle is slightly higher than that of the spray from the nozzle with a 30 degree pintle. The penetration of the sprays from the pintle nozzles, for comparable conditions of injection pressure and air density, is about the same as that of sprays from round-hole orifices. Increase in air density decreases the penetration in about the same ratio with all the injection pressures.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-465
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  • 86
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    A complete tank test of a model of a flying-boat hull-N.A.C.A. Model No.11 (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of comparison and application. A practical problem using the characteristics of model no.11 is presented to show the method of calculating the take-off time and run of a seaplane from these data.
    Type: NACA-TN-464
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  • 87
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    Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests were made of a model wing having an aspect ratio of 3 and a tapered plan form with a straight trailing edge. The model had the Clark Y airfoil section throughout it's entire span and had no washout, depending on a trailing-edge flap for longitudinal balance and control. The flap had a constant chord and was divided into four equal portions along the span. The tests were made with the entire flap deflected to obtain longitudinal control and balance, and also with the inner portions deflected alone, and with the outer portions deflected alone. It was found that the simple wing with no washout or change of basic section along the span has aerodynamic characteristics well suited for use on tailless airplanes. A higher lift coefficient was obtained with the full-span flap deflected as a unit to give longitudinal balance than was obtained with either the inner or the outer portions of the flap deflected.
    Type: NACA-TN-463
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  • 88
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    Formulas for the Stress Analysis of Circular Rings in a Monocoque Fuselage (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The formulas given in this report provide a simplified method for the stress-analysis of fuselage bulkheads that are approximately circular rings of uniform cross section. Complicated load systems acting on a ring can usually be resolved into simplified load systems; and formulas for moment, axial force, and shear for such simplified load systems are given in this report. Illustrative examples showing the use of this method in practical stress-analysis work are also included.
    Type: NACA-TN-462
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  • 89
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    Strength Tests of Thin-walled Duralumin Cylinders in Pure Bending (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the third of a series presenting the results of strengths tests on thin-walled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from pure bending tests on 58 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that the stress on the extreme fiber at failure as calculated by the ordinary theory of bending is from 30 to 80 percent greater than the compressive stress at failure for thin-walled cylinders in compression. The tests also show that length/radius ratio has no consistent effect upon the bending strength and that the size of the wrinkles that form on the compression half of a cylinder in bending is approximately equal to the size of the wrinkles that form in the complete circumference of a cylinder of the same dimensions in compression.
    Type: NACA-TN-479
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  • 90
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    The Effect of Rivet Heads on the Characteristics of a 6 by 36 Foot Clark Y Metal Airfoil (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the N.A.C.A. full-scale wind tunnel to determine the effects of exposed rivet heads on the aerodynamic characteristics of a metal-covered 6 by 36 foot Clasky airfoil. Lead punching simulating 1/8inch rivet heads were attached in full-span rows at a pitch of 1 inch at various chord positions. Tests were made at velocities varying from 40 to 120 miles per hour to investigate the scale effect. Rivets at the 5 percent chord position the upper surface of the airfoil produced the greatest increase in drag for a single row. Nine rows of rivets on both surfaces, simulating rivet spacing of multispan construction, increased the drag coefficients by a constant amount at velocities between 100 and 120 miles per hour. Accordingly, if rivets spaced the same as those on the test airfoil were used on a Clark Y wing of 300 square feet area and operated at 200 miles per hour, the drag would be increased over that for the smooth wing by 55 pounds and the power required would be increased by 29 horsepower.
    Type: NACA-TN-461
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  • 91
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    The Effects of Slots and Flaps on Lateral Control of a Low-wing Monoplane as Determined in Flight (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of flight tests made to determine the effect of slots and flaps on the lateral control of a low-wing monoplane. Maximum angular accelerations in roll and yaw produced by sudden application of the ailerons and maximum accelerations in yaw produced by sudden application of the rudder during gliding flight were recorded for the following wing arrangements: (a) no auxiliary device; (b) full-span slots; (c) plain flaps; (d) flaps and full-span slots; (e) wing-tip slots. Rolling- and yawing-moment coefficients were derived from the accelerations. The full span slots and the flaps each had about the same influence on the aileron rolling moments. At values of the lift coefficient obtainable with the plain wing, the effect of these devices was negligible. At the higher lift coefficients obtainable with these devices, the rolling-moment coefficients increased slightly but, despite this increase, the aileron effectiveness progressively decreased with increasing lift coefficient, owing to the corresponding reduction in air speed. In the range covered by the tests, the effectiveness of the controls was appreciably reduced by the wing-tip slots. The adverse yawing moment of the ailerons experienced at the large lift coefficients obtained with the flaps was appreciably less than at similar lift coefficients obtained with either full-span or wing-tip slots. The yawing moments produced by the rudder were only slightly affected by the use of the auxiliary devices. The airplane was found to be laterally unstable with all combinations tested. Because of the angular velocities acquired in the time taken to deflect the ailerons the rolling moments recorded in flight were only about two thirds the values that would have been obtained with the wing restrained as in wind-tunnel tests.
    Type: NACA-TN-478
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  • 92
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    The effect on engine performance of change in jacket-water outlet temperature (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests made on a Curtiss D-12 engine in the Altitude Laboratory at the Bureau of Standards show the following effects on engine performance of change in jacket-water outlet temperature: 1) Friction at all altitudes is a linear function of the jacket-water temperature, decreasing with increasing temperature. 2) The brake horsepower below an altitude of about 9,000 feet decreases, and at higher altitudes increases, with jacket-water temperature. 3) The brake specific fuel consumption tends to decrease, at all altitudes, with increasing jacket-water temperature. 4) The percentage change in brake power output is roughly equal to the algebraic sum of the percentage change in volumetric efficiency and mechanical efficiency.
    Type: NACA-TN-476
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  • 93
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    Full-scale Wind-tunnel Research on Tail Buffeting and Wing-fuselage Interference of a Low-wing Monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some preliminary results of full scale wind tunnel testing to determine the best means of reducing the tail buffeting and wing-fuselage interference of a low-wing monoplane are given. Data indicating the effects of an engine cowling, fillets, auxiliary airfoils of short span, reflexes trailing edge, propeller slipstream, and various combinations of these features are included. The best all-round results were obtained by the use of fillets together with the National Advisory Committee for Aeronautics (NACA) cowling. This combination reduced the tail buffeting oscillations to one-fourth of their original amplitudes, increased the maximum lift 11 percent, decreased the minimum drag 9 percent, and increased the maximum ratio of lift to drag 19 percent.
    Type: NACA-TN-460
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  • 94
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    Wind tunnel research comparing lateral control devices, particularly at high angles of attack XI : various floating tip ailerons on both rectangular and tapered wings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Discussed here are a series of systematic tests being conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present tests were made with six different forms of floating tip ailerons of symmetrical section. The tests showed the effect of the various ailerons on the general performance characteristics of the wing, and on the lateral controllability and stability characteristics. In addition, the hinge moments were measured for the most interesting cases. The results are compared with those for a rectangular wing with ordinary ailerons and also with those for a rectangular wing having full-chord floating tip ailerons. Practically all the floating tip ailerons gave satisfactory rolling moments at all angles of attack and at the same time gave no adverse yawing moments of appreciable magnitude. The general performance characteristics with the floating tip ailerons, however, were relatively poor, especially the rate of climb. None of the floating tip ailerons entirely eliminated the auto rotational moments at angles of attack above the stall, but all of them gave lower moments than a plain wing. Some of the floating ailerons fluttered if given sufficiently large deflection, but this could have been eliminated by moving the hinge axis of the ailerons forward. Considering all points including hinge moments, the floating tip ailerons on the wing with 5:1 taper are probably the best of those which were tested.
    Type: NACA-TN-458
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  • 95
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    The Aerodynamic Characteristics of Airfoils as Affected by Surface Roughness (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect on airfoil characteristics of surface roughness of varying degrees and types at different locations on an airfoil was investigated at high values of the Reynolds number in a variable density wind tunnel. Tests were made on a number of National Advisory Committee for Aeronautics (NACA) 0012 airfoil models on which the nature of the surface was varied from a rough to a very smooth finish. The effect on the airfoil characteristics of varying the location of a rough area in the region of the leading edge was also investigated. Airfoils with surfaces simulating lap joints were also tested. Measurable adverse effects were found to be caused by small irregularities in airfoil surfaces which might ordinarily be overlooked. The flow is sensitive to small irregularities of approximately 0.0002c in depth near the leading edge. The tests made on the surfaces simulating lap joints indicated that such surfaces cause small adverse effects. Additional data from earlier tests of another symmetrical airfoil are also included to indicate the variation of the maximum lift coefficient with the Reynolds number for an airfoil with a polished surface and with a very rough one.
    Type: NACA-TN-457
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  • 96
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    The Effect of Split Trailing-edge Wing Flaps on the Aerodynamic Characteristics of a Parasol Monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of tests conducted in the N.A.C.A. full-scale wind tunnel on a Fairchild F-22 airplane equipped with a special wing having split trailing-edge flaps. The flaps extended over the outer 90 percent of the wing span, and were of the fixed-hinge type having a width equal to 20 percent of the wing chord. The results show that with a flap setting of 59 degrees the maximum lift of the wing was increased 42 percent, and that the flaps increased the range of available gliding angles from 2.7 degrees to 7.0 degrees. Deflection of the split flaps did not increase the stalling angle or seriously affect the longitudinal balance of the airplane. With flaps down the landing speed of the airplane is decreased, but the calculated climb and level-flight performance is inferior to that with the normal wing. Calculations indicate that the take-off distance required to clear an obstacle 100 feet high is not affected by flap settings from 0 degrees to 20 degrees but is greatly increased by larger flap angles.
    Type: NACA-TN-475
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  • 97
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    The Aerodynamic Effect of a Retractable Landing Gear (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels were extended reduced the drag only 2 percent at a lift coefficient of 1.0, which was assumed for the take-off condition. Therefore, the wheel openings in the bottom side of the wing have a negligible effect upon the take-off of the airplane. Retracting the landing gear reduced the minimum drag of the complete airplane 50 percent.
    Type: NACA-TN-456
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  • 98
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    Effect of stabilizer location upon pitching and yawing moments in spins as shown by tests with the spinning balance (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made with the spinning balance in a 5-foot wind tunnel to study the effect of stabilizer location upon the pitching and yawing moments given by the tail surfaces in spinning attitudes. The tests revealed that the horizontal surfaces, when in a normal location, seriously reduced the effectiveness of the fin and rudder, particularly at angles of attack of 50 degrees or more. The tests also revealed that a more forward or more rearward location gave no consistent or decided improvement; that a lower location greatly increased the shielding so that the yawing moment from the combination was in general less than that given by the bare fuselage; and that a higher location decreased the shielding and gave a favorable interference effect, particularly at the high angles of attack. Additional results regarding the stabilizer and the elevator are given.
    Type: NACA-TN-474
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  • 99
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    Comparison of Three Methods for Calculating the Compressive Strength of Flat and Slightly Curved Sheet and Stiffener Combinations (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a comparison of the accuracy of the three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressed-skin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffener and an effective width as a column gave the best agreement with the results of the tests. An investigation of the effect of small curvature resulted in the conclusion that the compressive strength of the curved panels is, for all practical purposes, equal to the strength of flat panels except for thick sheet where non-uniform curvature throughout the length may cause the strength of the curved panel to be 10 to 15 percent less than that of a corresponding flat panel.
    Type: NACA-TN-455
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  • 100
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    Tank Tests of Two Floats for High-speed Seaplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: At the request of the Bureau of Aeronautics, Navy Department, a study of the design of floats especially suitable for use on high-speed seaplanes was undertaken in the N.A.C.A. tank. This note give the results obtained in tests of one-quarter full-size models of two floats for high-speed seaplanes. One was a float similar to that used on the Macchi high-speed seaplane which competed in the 1926 Schneider Trophy races, and the other a float designed at the N.A.C.A. tank in an attempt to improve on the water performance of the Macchi float. The model of the latter showed considerably better water performance than the model of the Macchi float.
    Type: NACA-TN-473
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