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  • Maps  (1)
  • Other Sources  (177)
  • 2010-2014
  • 1980-1984
  • 1925-1929  (178)
  • 1928  (178)
Collection
Source
Keywords
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Year
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  • 1
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    [Neue Nr. 6418] Birkenau / Geologische Karte (1928)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:6418 | Kart H 86:6418
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften der festen Erde), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: E 008 40 - E 008 50 / N 049 36 - N 049 30
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte ; Birkenau
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 77
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    CITATION GEO-LEO
  • 2
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    [Neue Nr. 5422] Herbstein / Geologische Karte (1928)
    Staatsverlag, Darmstadt
    In:  SUB Göttingen | KART B 104:5422 | KART H 86:5422
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: E 009 20 - E 009 30 /N 050 36 - N 050 30.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte ; Herbstein
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 112
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    CITATION GEO-LEO
  • 3
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    [Neue Nr. 6320] Michelstadt / Geologische Karte (1928)
    Hessische Geologische Landesanstalt, Darmstadt
    In:  SUB Göttingen | KART B 104:6320 | KART H 86:6319
    Details
    Publication Date: 2023-02-14
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: E 009 00 - E 009 10 / N 049 42 - N 049 36
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte ; Michelstadt
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 52
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    CITATION GEO-LEO
  • 4
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    Die Berechnung der Herdkoordinate eines Nahbebens (1928)
    In:  Gerlands Beitr. Geophys., Amsterdam, Schweizerbart'sche Verlagsbuchhandlung, vol. 19, no. 12, pp. 73-98, pp. L12S09, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1928
    Keywords: AUD ; Magnitude ; Location ; Seismology ; Nearfield
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Bodenunruhe durch Brandung und durch Frost (1928)
    In:  Zeitschrift für Geophysik, Jena, Gustav Fischer, vol. 4, no. 3, pp. 246-250, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1928
    Keywords: NOISE ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Das Aufsuchen von Bodenschätzen, insbesondere von Erzen, mit Hilfe der geophysikalischen Aufschlußmethoden (1928)
    In:  Metallwirtschaft, Jena, Gustav Fischer, vol. 7, no. 3, pp. 628-634, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1928
    Keywords: Applied geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Der Aufbau der Erdkruste in Europa (1928)
    In:  Geologische Rundschau, Jena, Gustav Fischer, vol. 19, no. 3, pp. 433-439, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1928
    Keywords: CRUST ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Mechanik und Thermodynamik des Erdkörpers: Bewegungen der Erdachse und Polwanderungen (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 709-719, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Earth model, also for more shallow analyses ! ; Earth rotation ; Fluids ; Geothermics
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Mechanik und Thermodynamik des Erdkörpers: Die Dichte der Erde und der Druck im Erdinnern (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 803-808, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Earth model, also for more shallow analyses ! ; Geothermics ; Fluids
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Bodenunruhe durch Brandung und durch Frost (1928)
    In:  Forschungen und Fortschritte, Jena, Gustav Fischer, vol. 4, no. 3, pp. 357-358, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1928
    Keywords: NOISE ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Geh. Reg.-Rat Prof. Dr. E. Wiechert† (1928)
    In:  Meteorologische Zeitschrift, Jena, Gustav Fischer, vol. 45, no. 3, pp. 183-185, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1928
    Keywords: Nachruf
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Mechanik und Thermodynamik des Erdkörpers: Beobachtungen über Schwere und Isostasie (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 697-709, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Gravimetry, Gravitation ; Fluids ; Geothermics
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Mechanik und Thermodynamik des Erdkörpers: Die Entwicklung der Erde (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 662-681, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Earth model, also for more shallow analyses ! ; Fluids ; Geothermics
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Die Abhängigkeit der Ernteerträge von den Witterungsfaktoren im Gebiet zwischen Saale, Mulde und Elbe (1928)
    In:  Vereinigten Friedrichs-Universität Halle-Wittenberg, Halle.
    Details
    Publication Date: 1928
    Description: Ertragsrelevante Korrelationen bei Winterweizen und -gerste mit der Temperatur, bei allen übrigen Kulturen war Niederschlag entscheidend KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Saalkreis, Kreis Bitterfeld, Kreis Delitzsch, Kreis Wittenberg, südl. Teil Kreis Köthen ; 1900-26 ; Kartoffeln ; Boden ; Ertrag ; Getreide ; Hafer ; Niederschlag ; Rangordnungsmethode ; Roggen ; Temperatur ; Weizen ; Witterung ; Hackfrüchte
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  • 15
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    Über die Temperaturabhängigkeiten von Insekten. 1. Über die Vorzugstemperatur einiger Insekten (1928)
    In:  Zeitschr. wiss. Biol. Abt. C. Vergl. Physiol. 8; p.1-16
    Details
    Publication Date: 1928
    Description: Der Autor beschreibt Laborversuche zur Ermittlung der Vorzugstemperatur von Tribolium confusum, Rhizoperta dominica, Capnodis carbonaria, Scanthius aegyptius und weiteren Insekten mit Hilfe einer Temperaturorgel. Die Insekten wurden dabei zudem noch unterschiedlichen Vorbehandlungen unterzogen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Labor ; 1926-28
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  • 16
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    Tausendkorngewicht und Witterung in den Jahren 1921 bis 1926 (1928)
    In:  Georgine, Königsberg 104 (10):65-66
    Details
    Publication Date: 1928
    Description: Einluß von Temperatur und Niederschlag in bestimmten Zeiträumen auf das Tausendkorngewicht (TKG) KATASTER-BESCHREIBUNG: Zusammenhang Niederschlag, Temperatur und Sonnenscheinstunden zum Tausendkorngewicht (Ertrag) von Weizen, Roggen und Gerste KATASTER-DETAIL: Delta T (0,48-1,9°C während der Vegetationszeit April-August über dem Mittel der Jahre 1921-26) und Delta Nied (-25- +52% vom Schossen bis zur Ernte über dem Mittel der Jahre 1921-26), dann höhreres TKG um 11,6-21,4%
    Keywords: Pommern ; 1921-1926 ; Ertrag ; Getreide ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Sonnenscheindauer ; Gerste
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  • 17
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    Frostgefährdung wintergrüner Gehölze (1928)
    In:  Mitt Deut. Dendrol. Gesell. 40: 175-184
    Details
    Publication Date: 1928
    Description: Diskussion über Winterschäden an immergrünen Bäumen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
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  • 18
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    Die Abhängigkeit der Ernteerträge von den Witterungsfaktoren im Gebiete zwischen Saale, Mulde und Elbe (1928)
    In:  Kühn-Archiv, Berlin, Band XX, Seite 223-301
    Details
    Publication Date: 1928
    Description: Auswertung von 27 Versuchsjahren, Bestimmung einer kritischen Periode für die Mindestniederschlagshöhe durch Auswertung der Klimaparmeter in einzelnen Bezirken mittels Rangkorrelationskoeffizienten KATASTER-BESCHREIBUNG: Zusammenhang zwischen der Niederschlagshöhe und dem Ertrag von Zuckerrüben, Zusammenhang zwischen der Sonnenscheindauer und dem Zuckergehalt von Zuckerrüben KATASTER-DETAIL: Delta Nied+: Nied 〉 175 mm (Juli-September), dann Ertragssteigerung bei ZR; Delta Sonn +: Sonn〉 4.43 h (September -Oktober), dann hohe Zuckergehalte bei ZR
    Keywords: Sachsen-Anhalt ; 1900-1926 ; Zuckerrüben ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Witterung
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  • 19
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    Das Klima in landwirtschaftlicher Beziehung (1928)
    In:  Vol. Band 2, No. 3, pp. 1-95-137.
    Details
    Publication Date: 1928
    Description: Einfluss der Temperatur, des Niederschlags, des Lichtes, Windes, Donner und Hagel auf das Pflanzenleben und Wachstum KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Niederschlag ; Temperatur ; Wachstum ; Sonnenscheindauer
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  • 20
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    Untersuchungen über die Abhängigkeit des pflanzlichen Wachstumsverlaufs und der Endlänge von konstanten Temperaturgeraden Schweizerbart, Stuttgarg. (1928)
    In:  Schweizerbart, Stuttgarg, 95 Seiten
    Details
    Publication Date: 1928
    Description: Einfluss der Temperatur auf das Pflanzenwachstum KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Temperatur ; Wachstum
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  • 21
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    Der Einfluss des Klimas auf die Landwirtschaft in Thüringen (1928)
    In:  Diss. Leipzig Weimar.
    Details
    Publication Date: 1928
    Description: Darstellung der Klimatologie Thüringens in Bezug zur Nutzung für die Pflanzenproduktion und die Tierproduktion KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Thüringen
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  • 22
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    Beitrag zur Kenntnis der Umwelteinflüsse auf die Kartoffeln unter besonderer Berücksichtigung der Sorteneigenschaften (1928)
    In:  Diss. Berlin.
    Details
    Publication Date: 1928
    Description: Versuche auf 13 Versuchsstationen, Einfluss des Wetters auf die Entwicklung, den etwaigen Krankheitsbefall, den Knollenertrag und den Stärkegehalt KATASTER-BESCHREIBUNG: Temperaturen während des Aufgangs für die Dauer des Aufgangs entscheidend, Verzögerung der Blüte bei nasser und kalter Witterung, insbesondere bei den frühen Sorten, Sonnenscheindauer für den Stärkegehalt entscheidend KATASTER-DETAIL: Delta T+ (〉5°C während des Aufgangs), dann Aufgang innerhalb von 3 Wochen, ansonsten bis 5.5 Wochen;
    Keywords: Deutschland, Versuchsstationen ; 1924-26 ; Kartoffeln ; Ertrag ; Niederschlag ; Temperatur ; Sonnenscheindauer
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  • 23
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    Einfluss der Witterungs-Erscheinungen auf die Erträge unserer Kulturpflanzen. (1928)
    In:  Deut. Landwirtschaflt. Presse 55:94-95.
    Details
    Publication Date: 1928
    Description: Übersicht über die Literatur zum Einfluss des Wetters auf die Kulturpflanzen KATASTER-BESCHREIBUNG: Milder und trockener Winter wirkt positiv auf die Weizenerträge, kalter und niederschlagsreicher Winter eher negativ, Betrachung für Norddeutschland KATASTER-DETAIL:
    Keywords: Deutschland ; 1900-1926 ; Kartoffeln ; Ertrag ; Getreide ; Hafer ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Trockenheit ; Witterung ; Gerste
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  • 24
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    Biometrical studies on the variation of physiologic forms of Puccinia graminis tritici and the effects of ecological factors on the susceptibility of wheat varieties (1928)
    In:  Phytopathology 18, No.1, p. 7-123
    Details
    Publication Date: 1928
    Description: Ergebnisse 5-jähriger Freilandversuche und 9-jähriger Laborversuche zu den Zusammenhängen zwischen klimatischen und anderen Umweltfaktoren und dem Auftreten verschiedener physiologischer Formen des Schwarzrostes an unterschiedlichen Weizensorten in den USA und Kanada. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: USA, Kanada ; 1919-1923 ; Getreide ; Pflanzenkrankheit ; Weizen
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  • 25
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    Über die Kettenlinie und die Exponentialkurve überhaupt als Bilder für die Abhängigkeit der Entwicklungsdauer von der Wärme (1928)
    In:  Zeitschr. angew. Entomol. 14, p.273-284
    Details
    Publication Date: 1928
    Description: Diskussion eines Populationsmodells für Insekten auf Basis einer Art Wärmesummenregel. Die Meßwerte zur Bildung des Modells wurden im Labor erhoben. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Labor ; 1926-28 ; Pflanzenschädling
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  • 26
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    Handbuch des Kartoffelbaus (1928)
    In:  P. Paray (Berlin), 317 Seiten
    Details
    Publication Date: 1928
    Description: Beziehung der Witterungseinflüsse auf die Knollenerträge, Auswertungen von Kartoffelkulturstationsergebnissen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1900-1925
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  • 27
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    Die Auswertung der Ernteerträge (1928)
    In:  Mitt. DLG, S. 128
    Details
    Publication Date: 1928
    Description: Zusammenhang zwischen der Witterung und den Knollenerträgen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Witterung
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  • 28
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    Der Maikäfer. Studien zur Biologie und zum Vorkommen im südlichen Mitteleuropa (1928)
    In:  Monographien zur angewandten Entomologie. In: Beihefte zur Zeitschrift für angewandte Entomologie, Nr.9, Beiheft zu Band 13; Parey, Berlin; 453p.
    Details
    Publication Date: 1928
    Description: Das Auftreten des Maikäfers in Österreich wird auf Ebene der Bundesländer aufgelöst anhand von Beobachtungsdaten betrachtet. Umfangreiches Kartenmaterial hierüber wurde erstellt. Es wird versucht Zusammenhänge mit klimatischen und anderen Parametern (z.B.Boden, Rassen) herzustellen. Eine Prognose des Maikäferauftretens auf Basis der Temperaturregeln und des 3- bzw. 4-jährigen Charakters der Maikäferpopulationen bis 2028 wird gegeben. KATASTER-BESCHREIBUNG: Zweigelt trägt Regeln aus der Literatur zusammen und verändert und diskutiert diese auf ihre Anwendbarkeit auf Maikäferpopulationen in Österreich hin. Er hebt die Bedeutung von Wärme, Regen und Schnee für das Maikäferschwärmen hervor; warmes, trockenes Klima ist notwendig, um den Käfer zum Massenschädling zu machen. KATASTER-DETAIL: - Tagestemp. von 20°C notwendig, um das Schwärmen einzuleiten (Erreichen nur einmal notwendig) - Erscheinen der ersten Käfer hängt von Frühlingstemp. ab - Maikäfer kommen zum Vorschein, wenn tmit 〉= 15°C und Summe der tmit ab 1.März erreicht 355°C - Jahresmittel von 7°C und Julimittel von 17,5°C dürfen nicht unterschritten werden - Temp.mittel (Apr-Okt) muss mind. 12,5°C betragen, damit sich Maikäfer zum Massenschädling entwickeln kann
    Keywords: Österreich, Deutschland ; 1909-1921 ; Forst ; Pflanzenschädling
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  • 29
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    Die Überwinterung der Obst- und Gemüsebauschädlinge (1928)
    In:  Landw. Wochenschr. Prov. Sachsen u. Anhalt, Nr. 41, p. 234
    Details
    Publication Date: 1928
    Description: verbale Beschreibung zur Überwinterungsmöglichkeit von Insekten, allgemeine Beschreibung KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Pflanzenschädling
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  • 30
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    The Relationship of Crop Yield and Weather (1928)
    In:  Nature 122:258.
    Details
    Publication Date: 1928
    Description: Berechnung partieller Korrelationskoeffizienten zwischen Temperatur, Niederschlag, Sonnenschein und Feuchte, in einzelnen Monaten KATASTER-BESCHREIBUNG: Erträge sind abhängig von Temperatur, Sonnenscheindauer, Niederschlag und Feuchte in der Zeit von April bis Juli in Norddakota und von April bis September in Ohio KATASTER-DETAIL:
    Keywords: Norddakota und Ohio ; 1920? ; Ertrag ; Korrelationsmethode ; Niederschlag ; Temperatur ; Globalstrahlung
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  • 31
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    Witterung und Gerstenerträge (1928)
    In:  Landw. Wochenschrift für die Provinz Sachsen und Anhalt, Hallle 18:428ff.
    Details
    Publication Date: 1928
    Description: Zusammenhang Witterung in Monaten und Gerstenertrag KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Sachsen und Anhalt ; 1920 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung
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  • 32
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    Untersuchungen über Beziehungen zwischen Witterung und Ernteertrag in der Landwirtschaft (1928)
    In:  Diss., Hohenheim.
    Details
    Publication Date: 1928
    Description: Beziehung zwischen Witterung (unterteilt in einzelne Monate) und Ertragshöhe mithilfe der Rangordnungs- und der Korrelationsmethode KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenscheindauer) auf den Ertrag von Winterweizen, Sommerweizen, Sommergerste, Wintergerste, Hafer und Runkelrüben auf dem Versuchsfeld (wasserundurchlässiger Boden) KATASTER-DETAIL: Delta Sonn (Oktober bis November)+, dann Erträge (Winterweizen) +; Delta Sonn (Dezember bis März)+, dann Erträge (Winterweizen) -; Delta Sonn (April) -, dann Erträge (Winterweizen) +; Delta Nied (April) +, dann Erträge (Winterweizen) +; Delta Nied (Mai, Juni und Juli) -, dann Erträge (Winterweizen) +; Delta Nied (August bis Oktober) +, dann Erträge (Winterweizen) +; Delta T (April) -, dann Erträge (Winterweizen) +; (Details sowie Informationen für Sommerweizen, Sommergerste, Wintergerste, Hafer und Runkelrüben siehe Artikel)
    Keywords: Hohenheim (Baden-Württemberg) ; 1914-25 ; Ertrag ; Getreide ; Hafer ; Klima ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Weizen ; Witterung ; Hackfrüchte
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  • 33
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    Der Einfluss von Trockenperioden auf die Sommerweizensorte 'ULCA' in verschiedenen Wachstumsstadien (1928)
    In:  Landw. Jahrbuch 68: 407-422
    Details
    Publication Date: 1928
    Description: Einfluss der Wasserversorgung in verschiedenen Wachstumsstadien auf die Entwicklung und die Ertragsfähigkeit der Sommerweizensorte 'Ulca' KATASTER-BESCHREIBUNG: Wasserstress hat in allen Vegetationsstadien ertragsrelevante Folgen KATASTER-DETAIL:
    Keywords: Labor ; 1926-27 ; Ertrag ; Wassermangel ; Weizen
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  • 34
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    Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde (1928)
    Vieweg
    In:  Braunschweig, Vieweg, vol. 10, no. 1, pp. 1-40, (ISBN 0-521-62272-7, ISBN 0-521-00600-7 paper)
    Details
    Publication Date: 1928
    Keywords: Handbook of geophysics ; Earth model, also for more shallow analyses ! ; Fluids ; Geothermics ; Gutenberg
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  • 35
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    Mechanik und Thermodynamik des Erdkörpers: Die Erdbeben (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 725-736, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Seismology ; Fluids ; Geothermics
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  • 36
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    Mechanik und Thermodynamik des Erdkörpers: Die elastischen Konstanten im Erdinnern (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 808-818, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Seismology ; Geothermics ; Velocity analysis ; Earth model, also for more shallow analyses ! ; Physical properties of rocks
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  • 37
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    Frankfurter Laufzeitkurven 1928 (one chart) (1928)
    Institut für Meteorologie und Geophysik
    In:  Frankfurt, Institut für Meteorologie und Geophysik, vol. 12, 189 S., no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1928
    Keywords: Seismology ; Travel time
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  • 38
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    Mechanik und Thermodynamik des Erdkörpers: Seismometrie (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 737-790, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Seismology ; Fluids ; Geothermics
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  • 39
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    Mechanik und Thermodynamik des Erdkörpers: Der Aufbau der Erde (Zusammenfassung) (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 818-827, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Earth model, also for more shallow analyses ! ; physical ; parameters ; of ; rocks ; Geothermics ; Velocity analysis ; Earth model, also for more shallow analyses ! ; Review article
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  • 40
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    Mechanik und Thermodynamik des Erdkörpers: Gezeiten des Erdkörpers (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 719-725, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Earth tides ; Seismology ; Fluids ; Geothermics
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  • 41
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    Mechanik und Thermodynamik des Erdkörpers: Die Gestalt der Erde (1928)
    Vieweg
    In:  Professional Paper, Müller - Pouillets Lehrbuch der Physik, Bd. 5.1 Physik der Erde, Braunschweig, Vieweg, vol. 3, no. VIIa, pp. 799-803, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1928
    Keywords: Earth model, also for more shallow analyses ! ; Fluids ; Geothermics ; Geodesy
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  • 42
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    Aeroelastic stability of wind turbine blades (1928)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The second degree nonlinear aeroelastic equations for a flexible, twisted, nonuniform wind turbine blade were developed using Hamilton's principle. The derivation of these equations has its basis in the geometric nonlinear theory of elasticity. These equations with periodic coefficients are suitable for determining the aeroelastic stability and response of large wind turbine blades. Methods for solving these equations are discussed.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Res. Center Wind Turbine Structural Dyn.; p 61-69
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  • 43
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    Bibliography of Aeronautics: 1926 (1928)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: This Bibliography of Aeronautics for 1926 covers the aeronautical literature published from January 1 to December 31, 1926. The first Bibliography of Aeronautics was published by the Smithsonian Institution as volume 55 of the Smithsonian Miscellaneous Collections and covered the material published prior to June 30, 1909. Supplementary volumes of the Bibliography of Aeronautics for the subsequent years have been published by the National Advisory Committee for Aeronautics. The last preceding volume was for the calendar year 1925. As in the previous volumes, citations of the publications of all nations are included in the languages in which these publications originally appeared. The arrangement is dictionary form with author find subject entry, and one alphabetical arrangement. Detail in the matter of subject reference has been omitted on aCC01.mt of the cost of presentation, but an attempt has been made to give sufficient cross reference for research in special lines.
    Keywords: Aeronautics (General)
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  • 44
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    Bibliography of Aeronautics: 1928 (1928)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: This Bibliography of Aeronautics for 1928 covers the aeronautical literature published from January 1 to December 31, 1928. The first Bibliography of Aeronautics was published by the Smithsonian Institution as volume 55 of the Smithsonian Miscellaneous Collections and covered the material published prior to June 30, 1909. Supplementary volumes of the Bibliography of Aeronautics for the subsequent years have been published by the National Advisory Committee for Aeronautics. The last preceding volume was for the calendar year 1927. As in the previous volumes, citations of the publications of all nations are included in the languages in which these publications originally appeared. The arrangement is in dictionary form with author and subject entry, and one alphabetical arrangement. Detail in the matter of subject reference has been omitted on account of the cost of presentation, but an attempt has been made to give sufficient cross reference for research in special lines.
    Keywords: Aeronautics (General)
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  • 45
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    The Measurement of Pressure Through Tubes in Pressure Distribution Tests (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this report were made to determine the error caused by using small tubes to connect orifices on the surface of aircraft to central pressure capsules in making pressure distribution tests. Aluminum tubes of 3/16-inch inside diameter were used to determine this error. Lengths from 20 feet to 226 feet and pressures whose maxima varied from 2 inches to 140 inches of water were used. Single-pressure impulses for which the time of rise of pressure from zero to a maximum varied from 0.25 second to 3 seconds were investigated. The results show that the pressure recorded at the capsule on the far end of the tube lags behind the pressure at the orifice end and experiences also a change in magnitude. For the values used in these tests the time lag and pressure change vary principally with the time of rise of pressure from zero to a maximum and the tube length. Curves are constructed showing the time lag and pressure change. Empirical formulas are also given for computing the time lag. Analysis of pressure distribution tests made on airplanes in flight shows that the recorded pressures are slightly higher than the pressures at the orifice and that the time lag is negligible. The apparent increase in pressure is usually within the experimental error, but in the case of the modern pursuit type of airplane the pressure increase may be 5 per cent. For pressure-distribution tests on airships the analysis shows that the time lag and pressure change may be neglected.
    Type: NACA-TR-270
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  • 46
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    Factors in the Design of Centrifugal Type Injection Valves for Oil Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This research was undertaken in connection with a general study of the application of the fuel injection engine to aircraft. The purpose of the investigation was to determine the effect of four important factors in the design of a centrifugal type automatic injection valve on the penetration, general shape, and distribution of oil sprays. The general method employed was to record the development of single sprays by means of special high-speed photographic apparatus capable of taking 25 consecutive pictures of the moving spray at a rate of 4,000 per second. Investigations were made concerning the effects on spray characteristics, of the helix angle of helical grooves, the ratio of the cross-sectional area of the orifice to that of the grooves, the ratio of orifice length to diameter, and the position of the seat. Maximum spray penetration was obtained with a ratio of orifice length to diameter of about 1.5. Slightly greater penetration was obtained with the seat directly before the orifice.
    Type: NACA-TR-268
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  • 47
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    Characteristics of propeller sections tested in the variable density wind tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were carried out in the variable density wind tunnel of the National Advisory Committee for Aeronautics on six airfoil sections used by the Bureau of Aeronautics as propeller sections. The sections were tested at pressures of 1 and 20 atmospheres corresponding to Reynolds numbers of about 170,000 and 3,500,000. The results obtained, besides providing data for the design of propellers, should be of special interest because of the opportunity afforded for the study of scale effect on a family of airfoil sections having different thickness ratios. (author)
    Type: NACA-TR-259
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  • 48
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    Pressure Distribution over a Wing and Tail Rib of a VE-7 and of a TS Airplane in Flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made to determine the pressure distribution over a rib of the wing and over a rib of the horizontal tail surface of an airplane in flight and to obtain information as to the time correlation of the loads occurring on these ribs. Two airplanes, VE-7 and TS, were selected in order to obtain the information for a thin and a thick wing section. In each case the pressure distribution was recorded for the full range of angle of attack in level flight and throughout violent maneuvers. The results show: (a) that the present rib load specifications in use by the Army Air Corps and the Bureau of Aeronautics, Navy Department, are in fair agreement with the loads actually occurring in flight, but could be slightly improved; (b) that there appears to be no definite sequence in which wing and tail surface ribs reach their respective maximum loads in different maneuvers; (c) that in accelerated flight, at air speeds less than or equal to 60 per cent of the maximum speed, the accelerations measured agree very closely with the theoretically possible maximum accelerations. In maneuvers at higher air speeds the observed accelerations were smaller than those theoretically possible. (author)
    Type: NACA-TR-257
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  • 49
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    Preliminary biplane tests in the variable density wind tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Biplane cellules using the N.A.C.A.-M6 airfoil section have been tested in the variable density wind tunnel of the National Advisory Committee for Aeronautics. Three cellules, differing only in the amount of stagger, were tested at two air densities, corresponding to pressures of one atmosphere and of twenty atmospheres. The range of angle of attack was from -2 degrees to +48 degrees. The effect of stagger on the lift and drag, and on the shielding effect of the upper wing by the lower at high angles of attack was determined.
    Type: NACA-TN-289
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  • 50
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    The reaction on a float bottom when making contact with water at high speeds (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted to investigate the possibility of a serious accident arising from unintentional contact with the water in substantially horizontal flight at high speed. Referring to vector diagrams on Figure 2, it will be seen that a very dangerous condition may arise if the float be allowed to come in contact with the water at high speeds as, for example, when flying at high speed just above the water. The initial diving moment due to suction and drag combined may be great enough to cause the seaplane to nose under before the pilot is able to control the motion. The same test data indicate clearly the existence of forces and moments tending to produce the phenomenon observed by Mr. Carroll (Technical Note No. 287) when the maneuver is carried out at lower speeds, as in a landing.
    Type: NACA-TN-288
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  • 51
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    A dangerous seaplane landing condition (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A peculiar phenomena in seaplane landing is observed and reported. The seaplane having executed a normal fast landing at low incidence, a forward movement of the control stick effected an unusual condition in that the seaplane left the water suddenly in an abnormal attitude. The observations describing this phenomena are offered as a warning against possible accident and as a conjectural cause of seaplane landing accidents of a certain kind.
    Type: NACA-TN-287
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  • 52
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    Preliminary Investigation on Boundary Layer Control by Means of Suction and Pressure with the U.S.A. 27 Airfoil (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this report constitute a preliminary investigation of airfoil boundary layer control, as carried out in the atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory, from February to August, 1927. Tests were made on a U.S.A. 27 airfoil section with various slot shapes and combinations, and at various amounts of pressure or suction on the slots. The lift of airfoils can be increased by removing or by accelerating the boundary layer. Removing the boundary layer by suction is more economical than to accelerate it by jet action. Gauze-covered suction slots apparently give the best results. When not in operation, all suction slots tested had a detrimental effect upon the aerodynamic characteristics of the airfoil which was not apparent with the backward-opening pressure slots. Thick, blunt-nose airfoils would seem to give best results with boundary layer control.
    Type: NACA-TN-286
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  • 53
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    Corrosion Embrittlement of Duralumin IV : The Use of Protective Coatings (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Although the corrosion resistance of sheet duralumin can be greatly improved by suitable heat treatment, protection of the surface is still necessary if long life under varied service conditions is to be insured. The coatings used for this purpose may be grouped into three classes: the varnish type of coating, the oxide type produced by a chemical treatment of the surface, and metallic coatings, of which aluminum appears to be the most promising. Since the necessary weather exposure tests are not complete, some of the conclusions regarding the value of various surface coatings are necessarily tentative.
    Type: NACA-TN-285
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  • 54
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    Corrosion Embrittlement of Duralumin III Effect of the Previous Treatment of Sheet Material on the Susceptibility to This Type of Corrosion (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a result of testing, it was determined that control of the rate of quenching and the avoidance of accelerated aging by heating are the only means of modifying duralumin itself so as to minimize the intercrystalline form of corrosive attack. It is so simple a means that it should be adopted even though it may not completely prevent, but only reduce, this form of corrosive attack. By so doing, the need for protection of the surface is less urgent.
    Type: NACA-TN-284
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  • 55
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    Corrosion Embrittlement of Duralumin II Accelerated Corrosion Tests and the Behavior of High-Strength Aluminum Alloys of Different Compositions (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The permanence, with respect to corrosion, of light aluminum alloy sheets of the duralumin type, that is, heat-treatable alloys containing Cu, Mg, Mn, and Si is discussed. Alloys of this type are subject to surface corrosion and corrosion of the interior by intercrystalline paths. Results are given of accelerated corrosion tests, tensile tests, the effect on corrosion of various alloying elements and heat treatments, electrical resistance measurements, and X-ray examinations.
    Type: NACA-TN-283
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  • 56
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    Corrosion Embrittlement of Duralumin I Practical Aspects of the Problem (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Since aircraft design is tending toward all-metal construction, the strong heat-treatable light aluminum alloy, duralumin (a generic name for a class of heat-treatable alloys containing Cu, Mg, Mn, and Si), is finding increasing application. Doubt has been expressed concerning the reliability and permanence of these materials. Information is given on the effect of corrosion on the tensile properties of 14-gauge sheet duralumin, heat treated by quenching in hot water after being heated for 15 minutes in a fused nitrate bath at 500 to 510 C. Intercrystalline corrosion and practical aspects of intercrystalline embrittlement are discussed with respect to duralumin.
    Type: NACA-TN-282
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  • 57
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    A Comparison of Propeller and Centrifugal Fans for Circulating the Air in a Wind Tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this paper afford a direct comparison of the efficiency and smoothness of flow obtained with propeller fan and multiblade centrifugal fan drives in the same wind tunnel. The propeller fan was found to be superior to the centrifugal fan in that the efficiency was about twice as great, and the flow much smoother.
    Type: NACA-TN-281
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  • 58
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    Drag and Cooling with Various Forms of Cowling for a Whirlwind Engine in a Cabin Fuselage (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation on the cowling of radial air-cooled engines was conducted in the 20-foot Propeller Research Tunnel at Langley Field. Cooling and drag tests were made with each form of cowling. The propulsive efficiency was found to be practically the same with all forms of cowling.
    Type: NACA-TN-301
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  • 59
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    Drag of Exposed Fittings and Surface Irregularities on Airplane Fuselages (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements of drag were made on fittings taken from a typical fuselage to determine whether the difference between the observed full size fuselage drag and model fuselage drag could be attributed to the effects of fittings and surface irregularities found on the full size fuselage and not on the model. There are wide variations in the drag coefficients for the different fittings. In general those which protrude little from the surface or are well streamlined show very low and almost negligible drag. The measurements show, however, that a large part of the difference between model and full scale test results may be attributed to these fittings.
    Type: NACA-TN-280
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  • 60
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    The variation in pressures in the cockpit fan airplane in flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of an investigation to determine the pressures in the open cockpit of a Vought VE-7 airplane are given. The observed values are small and the effect upon instruments is inconsiderable.
    Type: NACA-TN-300
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  • 61
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    Resistance of streamline wires (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note contains the results of tests to determine the resistance of four sizes of streamline wire. The investigation was conducted in the six-inch wind tunnel of the National Advisory Committee for Aeronautics. The tests were made at various velocities and it was found that the resistance of streamline wires was considerably less than that of round wires of equivalent strength. Scale effect was also found since, with an increase of Reynolds Number, a decrease in the resistance coefficient was obtained.
    Type: NACA-TN-279
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  • 62
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    The Effect of Fillets Between Wings and Fuselage on the Drag and Propulsive Efficiency of an Airplane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made to determine the effect of fillets between wings and fuselage on the drag and propulsive efficiency of a high-wing cabin monoplane. These tests were made in the 20-foot Propeller Research Tunnel of the National Advisory Committee for Aeronautics.
    Type: NACA-TN-299
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  • 63
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    The Determination of Several Spray Characteristics of a High-Speed Oil Engine Injection System with an Oscilloscope (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to determine the injection lag, duration of injection, and spray start and cut-off characteristics of a fuel injection system operated on an engine and injecting fuel into the atmosphere.
    Type: NACA-TN-298
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  • 64
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    An Automatic Speed Control for Wind Tunnels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Described here is an automatic control that has been used in several forms in wind tunnels at the Washington Navy Yard. The form now in use with the 8-foot tunnel at the Navy Yard is considered here. Details of the design and operation of the automatic control system are given. Leads from a Pitot tube are joined to an inverted cup manometer located above a rheostat. When the sliding weight of this instrument is set to a given notch, say for 40 m.p.h, the beam tip vibrates between two electric contacts that feed the little motor. Thus, when the wind is too strong or too weak, the motor automatically throws the rheostat slide forward and backward. If it failed to function well, the operator would notice the effect on his meniscus, and would operate the hand control by merely pressing the switch.
    Type: NACA-TN-278
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  • 65
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    Pressure distribution on wing ribs of the VE-7 and TS airplanes in flight Part II : pull-ups (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the second of a series of notes, each of which presents the complete results of pressure distribution tests made at Langley Field by the National Advisory Committee for Aeronautics, on wing and tail ribs of the VE-7 and TS airplanes for a particular maneuver of flight. The results for pull-ups are presented in the form of curves which show the variation of pressure distribution, total loads, normal acceleration and center of pressure with respect to time.
    Type: NACA-TN-277
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  • 66
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    Preliminary report on the flat-top lift curve as a factor in control at low speed (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the importance of the flat-top lift curve as a factor contributing to safety and control at low speed. An analysis of existing airfoil data indicated definite relations between the shape of the lift curve and certain section dimensions.
    Type: NACA-TN-297
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  • 67
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    Helium tables. (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These tables are intended to provide a standard method and to facilitate the calculation of the quantity of "Standard Helium" in high pressure containers. The research data and the formulas used in the preparation of the tables were furnished by the Research Laboratory of Physical Chemistry, of the Massachusetts Institute of Technology.
    Type: NACA-TN-276
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  • 68
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    Bearing strength of wood under steel aircraft bolts and washers and other factors influencing fitting design (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this report is to correlate, bring up to date, and put under a single cover all the information thought to be essential to an understanding of the formulas.
    Type: NACA-TN-296
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  • 69
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    Determination of Propeller Deflection by Means of Static Load Tests on Models (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note describes a simple and inexpensive method for determining the deflection of propeller blades under operating loads. Both the centrifugal force and air force loads are applied statically as a number of concentrated loads by means of weights and wires. Two methods of attaching the wires to the propeller blades have been tested, both giving approximately the same deflections. The method is considered useful for studying the deflections of propellers of different shapes under various operating conditions.
    Type: NACA-TN-275
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  • 70
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    The effect of tip shields on a horizontal tail surface (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of experiments made in the wind tunnel of the Daniel Guggenheim School of Aeronautics, New York University, on the effect of tip shields on a horizontal tail surface are described and discussed. It was found that some aerodynamic gain can be obtained by the use of tip shields though it is considered doubtful whether their use would be practical.
    Type: NACA-TN-295
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  • 71
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    The Effect of the Sperry Messenger Fuselage on the Air Flow at the Propeller Plane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to study the effect of the fuselage, landing gear, and engine on the air flow through the propeller, a survey was made in the plane of the Sperry Messenger propeller with the propeller removed. The tests were made in the 20-foot air stream of the propeller research tunnel of the National Advisory Committee for Aeronautics at Langley Field, Virginia. The variation of the velocity with distance from the center in the propeller plane was found to be appreciable and well worth consideration in the design of propellers. It was also found that the velocity through the propeller plane was affected by the presence of the engine, and that the velocity in front of the landing gear was lower than that at other points in the propeller plane having the same radius.
    Type: NACA-TN-274
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  • 72
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    The Drag of a J-5 Radial Air-Cooled Engine (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note describes tests of the drag due to a Wright "Whirlwind" (J-5) radial air-cooled engine mounted on a cabin type airplane. The tests were made in the 20-foot Propeller Research Tunnel of the National Advisory Committee for Aeronautics. The drag was obtained with three different types of exhaust stacks: Short individual stacks, a circular cross section collector ring, and a streamline cross section collector ring.
    Type: NACA-TN-292
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  • 73
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    Wind tunnel force tests in wing systems through large angles of attack (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Force tests on a systematic series of wing systems over a range of angle of attack from minus forty-five degrees to plus ninety degrees are covered in this report. The investigation was made on monoplane and biplane wing models to determine the effects of variations of tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweepback, and airfoil profile.
    Type: NACA-TN-294
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  • 74
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    The Effect on Performance of a Cutaway Center Section (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The assumption is made that a skeleton or cutaway center section is desirable for forward vision and to determine the effect of such mutilation upon performance the following work was done. The airplane used was a Vought VE-7 and in addition to the cutaway center section a system of end plates or fins was installed. Various conditions and combinations were investigated in level flight and in climb. It is found that the greatest difference in the conditions investigated was a drop of 12.5 per cent in a 10-minute climb while the effect upon level speeds was negligible.
    Type: NACA-TN-273
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  • 75
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    The Formation of Ice upon Exposed Parts of an Airplane in Flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to experimentally study the conditions leading to ice formation on aircraft surfaces, an aircraft was equipped with small auxiliary surfaces and aerodynamic shapes similar to struts, wires, Pitot heads, etc. This airplane was flown at an altitude where a temperature of 32 F was encountered, at such times as cloud formations could be found at the coincident altitude. Here it was discovered that ice formed rapidly in regard to quantity,character, shape, and rapidity of formation. An examination of this data, which confirms observations of pilots, indicates that the weight of ice collected can very possibly be sufficient to force the airplane to rapidly lose altitude on account of the increased loads. However, it is more evident that the malformation of the aerodynamic shapes may so increase the drag and reduce the lift so as to produce a loss of altitude even greater in consequence, the combination of the two working in the same direction having a double effect. Other adverse consequences are noted. The recommendation for the guidance of those who must encounter these conditions appears to lie entirely along the lines of avoidance.
    Type: NACA-TN-293
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  • 76
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    Special Propeller Protractor (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A special protractor was designed and built with a view towards supplying a simple, inexpensive, practical, portable instrument for making measurements to detect propeller warpage under practically all conditions, without the use of auxiliary equipment, and without having to remove the propeller from the airplane. A detailed description is given of the protractor. Techniques for measuring are described. Directions are given on how to use the protractor to set detachable blade-type propellers on an airplane.
    Type: NACA-TN-272
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  • 77
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    Full Scale Drag Tests on Various Parts of Sperry Messenger Airplane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag of a Sperry Messenger airplane with the wings removed, and also the drag of its various component parts, was measured in the 20-foot air stream of the N.A.C.A. propeller research tunnel at air speeds from 50 to 100 m.p.h. It was found that the three-cylinder radial air-cooled engine nearly doubled the drag of the bare fuselage, and the drag of the landing gear was about the same as that of the fuselage and engine combined.
    Type: NACA-TN-271
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  • 78
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    Gluing Practice at Aircraft Manufacturing Plants (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report records observations and recommendations resulting from an inspection trip to representative aircraft manufacturing establishments and repair stations. This inspection was made for the Navy Department and was specifically in reference to gluing practice at the various places visited. The period of the visits was between November 23, 1926 and February 16, 1927.
    Type: NACA-TN-291
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  • 79
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    Welding of high chromium steels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A brief description is given of different groups of high chromium steels (rustless iron and stainless steels) according to their composition and more generally accepted names. The welding procedure for a given group will be much the same regardless of the slight variations in chemical composition which may exist within a certain group. Information is given for the tensile properties (yield point and ultimate strength) of metal sheets and welds before and after annealing on coupons one and one-half inches wide. Since welds in rustless iron containing 16 to 18 percent chromium and 7 to 12 percent nickel show the best combination of strength and ductility in the 'as welded' or annealed condition, it is considered the best alloy to use for welded construction.
    Type: NACA-TN-290
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  • 80
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    Friction of Aviation Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The first portion of this report discusses measurements of friction made in the altitude laboratory of the Bureau of Standards between 1920 and 1926 under research authorization of the National Advisory Committee for Aeronautics. These are discussed with reference to the influence of speed, barometric pressure, jacket-water temperature, and throttle opening upon the friction of aviation engines. The second section of the report deals with measurements of the friction of a group of pistons differing from each other in a single respect, such as length, clearance, area of thrust face, location of thrust face, etc. Results obtained with each type of piston are discussed and attention is directed particularly to the fact that the friction chargeable to piston rings depends upon piston design as well as upon ring design. This is attributed to the effect of the rings upon the thickness and distribution of the oil film which in turn affects the friction of the piston to an extent which depends upon its design.
    Type: NACA-TR-262
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  • 81
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    Some Factors Affecting the Reproducibility of Penetration and the Cut-Off of Oil Sprays for Fuel-injection Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was undertaken at the Langley Memorial Aeronautical Laboratory in connection with a general research on fuel-injection for aircraft. The purpose of the investigation was to determine the factors controlling the reproducibility of spray penetration and secondary discharges after cut-off. The development of single sprays from automatic injection valves was recorded by means of special high-speed photographic apparatus capable of taking 25 consecutive pictures of the moving spray at a rate of 4,000 per second. The effect of two types of injection valves, injection-valve tube length, initial pressure in the injection-valve tube, speed of the injection control mechanism, and time of spray cut-off, on the reproducibility of spray penetration, and on secondary discharges were investigated. It was found that neither type of injection valve materially affected spray reproducibility. The initial pressure in the injection-valve tube controlled the reproducibility of spray penetrations. An increase in the initial pressure or in the length of the injection-valve tube slightly increased the spray penetration within the limits of this investigation. The speed of the injection-control mechanism did not affect the penetration. Analysis of the results indicates that secondary discharges were caused in this apparatus by pressure waves initiated by the rapid opening of the cut-off valve. The secondary discharges were eliminated in this investigation by increasing the length of the injection-valve tube. (author)
    Type: NACA-TR-258
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  • 82
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    Tests on Models of Three British Airplanes in the Variable Density Wind Tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the results of tests made in the National Advisory Committee for Aeronautics variable density wind tunnel on three airplane models supplied by the British Aeronautical Research Committee. These models, the BE-2E with R.A.F. 19 wings, the British Fighter with R.A.F. 15 wings, and the Bristol Fighter with R.A.F. 30 wings, were tested over a wide range in Reynolds numbers in order to supply data desired by the Aeronautical Research Committee for scale effect studies. The maximum lifts obtained in these tests are in excellent agreement with the published results of British tests, both model and full scale. No attempt is made to compare drag data, owing to the emission of tail surfaces, radiator, etc., from the model, but is shown that the scale effect observed on the drag coefficients in these tests is due to a large extent to the parts of the models other than the wings. (author)
    Type: NACA-TR-279
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  • 83
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    The Gaseous Explosive Reaction : The Effect of Inert Gases (1928)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: Attention is called in this report to previous investigations of gaseous explosive reactions carried out under constant volume conditions, where the effect of inert gases on the thermodynamic equilibrium was determined. The advantage of constant pressure methods over those of constant volume as applied to studies of the gaseous explosive reaction is pointed out and the possibility of realizing for this purpose a constant pressure bomb mentioned. The application of constant pressure methods to the study of gaseous explosive reactions, made possible by the use of a constant pressure bomb, led to the discovery of an important kinetic relation connecting the rate of propagation of the zone of explosive reaction within the active gases, with the initial concentrations of those gases: s = K(sub 1)(A)(sup n1)(B)(sup n2)(C)(sup n3)------. By a method analogous to that followed in determining the effect of inert gases on the equilibrium constant K, the present paper records an attempt to determine their kinetic effect upon the expression given above.
    Type: NACA-TR-280
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  • 84
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    Propeller problems (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report tries to give a comprehensive survey of the most important propeller problems such as the shape of propellers and the effect of atmospheric conditions on propeller performance.
    Type: NACA-TM-491
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  • 85
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    Aerodynamic characteristics of thin empirical profiles and their application to the tail surfaces and ailerons of airplanes (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-493
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  • 86
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    Characteristics of Five Propellers in Flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made for the purpose of determining the characteristics of five full-scale propellers in flight. The equipment consisted of five propellers in conjunction with a VE-7 airplane and a Wright E-2 engine. The propellers were of the same diameter and aspect ratio. Four of them differed uniformly in thickness and pitch and the fifth propeller was identical with one of the other four with exception of a change of the airfoil section. The propeller efficiencies measured in flight are found to be consistently lower than those obtained in model tests. It is probable that this is mainly a result of the higher tip speeds used in the full-scale tests. The results show also that because of differences in propeller deflections it is difficult to obtain accurate comparisons of propeller characteristics. From this it is concluded that for accurate comparisons it is necessary to know the propeller pitch angles under actual operating conditions. (author)
    Type: NACA-TR-292
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  • 87
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    Differential Pressures on a Pitot-venturi and a Pitot-static Nozzle over 360 Degrees Pitch and Yaw (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements of the differential pressures on two navy air-speed nozzles, consisting of a Zahm type Pitot-Venturi tube and a SQ-16 two-pronged Pitot-static tube, in a tunnel air stream of fixed speed at various angles of pitch and yaw between 0 degrees and plus or minus 180 degrees. This shows for a range over -20 degrees to +20 degrees pitch and yaw, indicated air speeds varying very slightly over 2 per cent for the Zahm type and a maximum of about 5 per cent for the SQ-16 type from the calibrated speed at 0 degree. For both types of air-speed nozzle the indicated air speed increases slightly as the tubes are pitched or yawed several degrees from their normal 0 degrees altitude, attains a maximum around plus or minus 15 degrees to 25 degrees, declines rapidly therefrom as plus or minus 40 degrees is passed, to zero in the vicinity of plus or minus 70 degrees to 100 degrees, and thence fluctuates irregular from thereabouts to plus or minus 180 degrees. The complete variation in indicated air speed for the two tubes over 360 degree pitch and yaw is graphically portrayed in figures 9 and 10. For the same air speed and 0 degree pitch and yaw the differential pressure of the Zahm type Pitot-Venturi nozzle is about seven times that of the SQ-16 type two-prolonged Pitot-static nozzle.
    Type: NACA-TR-264
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  • 88
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    Performance of Several Combustion Chambers Designed for Aircraft Oil Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several investigations have been made on single-cylinder test engines to determine the performance characteristics of four types of combustion chambers designed for aircraft oil engines. Two of the combustion chambers studied were bulb-type precombustion chambers, the connecting orifice of one having been designed to produce high turbulence by tangential air flow in both the precombustion chamber and the cylinder. The other two were integral combustion chambers, one being dome-shaped and the other pent-roof shaped. The injection systems used included cam and eccentric driven fuel pumps, and diaphragm and spring-loaded fuel-injection valves. A diaphragm type maximum cylinder pressure indicator was used in part of these investigations with which the cylinder pressures were controlled to definite valves. The performance of the engines when equipped with each of the combustion chambers is discussed. The best performance for the tests reported was obtained with a bulb-type combustion chamber designed to give a high degree of turbulence within the bulb and cylinder. (author)
    Type: NACA-TR-282
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  • 89
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    The Effects of Fuel and Cylinder Gas Densities on the Characteristics of Fuel Sprays for Oil Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted as a part of a general research on fuel-injection engines for aircraft. The purpose of the investigation was to determine the effects of fuel and cylinder gas densities with several characteristics of fuel sprays for oil engines. The start, growth, and cut-off of single fuel sprays produced by automatic injection valves were recorded on photographic film by means of special high-speed motion-picture apparatus. This equipment, which has been described in previous reports, is capable of taking twenty-five consecutive pictures of the moving spray at the rate of 4,000 per second. The penetrations of the fuel sprays increased and the cone angles and relative distributions decreased with increase in the specific gravity of the fuel. The density of the gas into which the fuel sprays were injected controlled their penetration. This was the only characteristic of the chamber gas that had a measurable effect upon the fuel sprays. Application of fuel-spray penetration data to the case of an engine, in which the pressure is rising during injection, indicated that fuel sprays may penetrate considerably farther than when injected into a gas at a density equal to that of the gas in an engine cylinder at top center.
    Type: NACA-TR-281
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  • 90
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    Lift, Drag, and Elevator Hinge Moments of Handley Page Control Surfaces (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report combines the wind tunnel results of tests on four control surface models made in the two wind tunnels of the Navy Aerodynamic Laboratory, Washington Navy Yard, during the years of 1922 and 1924, and submitted for publication to the National Advisory Committee for Aeronautics May 7, 1927. The purpose of the tests was to compare, first, the lifts and the aerodynamic efficiencies of the control surfaces from which their relative effectiveness as tail planes could be determined; then the elevator hinge moments upon which their relative ease of operation depended. The lift and drag forces on the control surface models were obtained for various stabilizer angles and elevator settings in the 8 by 8 foot tunnel by the writer in 1922; the corresponding hinge moments were found in the 4 by 4 foot tunnel by Mr. R. M. Bear in 1924. (author)
    Type: NACA-TR-278
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  • 91
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    The Effect of the Walls in Closed Type Wind Tunnels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of tests has been conducted during the period 1925-1927 by the National Advisory Committee for Aeronautics in the variable-density wind tunnel on several airfoil models of different sizes and sections to determine the effect of tunnel-wall interference and to determine a correction which can be applied to reduce the error caused thereby. The use of several empirical corrections was attempted with little success. The Prandtl theoretical corrections give the best results, and their use is recommended for correcting closed wind tunnel results to the conditions of free air. An appendix is attached wherein the experimentally determined effect of the walls on the tunnel velocity very close to their surface is given. This is of special interest because a "scale effect" was found in the boundary layer with a change in the density of the tunnel air.
    Type: NACA-TR-275
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  • 92
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    Structures of Thin Sheet Metal, Their Design and Construction (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a brief survey of the uses of sheet-metal coverings in conjunction with the inner structure. A method of construction is presented as well as a discussion on the strength of sheet metal.
    Type: NACA-TM-490
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  • 93
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    The comparative performance of an aviation engine at normal and high inlet air temperatures (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents some results obtained during an investigation to determine the effect of high inlet air temperature on the performance of a Liberty 12 aviation engine. The purpose of this investigation was to ascertain, for normal service carburetor adjustments and a fixed ignition advance, the relation between power and temperature for the range of carburetor air temperatures that may be encountered when supercharging to sea level pressure at altitudes of over 20,000 feet and without intercooling when using plain aviation gasoline and mixtures of benzol and gasoline. The results show that for the conditions of test, both the brake and indicated power decrease with increase in air temperature at a faster rate than given by the theoretical assumption that power varies inversely as the square root of the absolute temperature. On a brake basis, the order of the difference in power for a temperature difference of 120 degrees F. Is 3 to 5 per cent. The observed relation between power and temperature when using the 30-70 blend was found to be linear. But, although these differences are noted, the above theoretical assumption may be considered as generally applicable except where greater precision over a wide range of temperatures is desired, in which case it appears necessary to test the particular engine under the given conditions. (author)
    Type: NACA-TR-277
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  • 94
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    The N.A.C.A. Photographic Apparatus for Studying Fuel Sprays from Oil Engine Injection Valves and Test Results from Several Researches (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Apparatus for recording photographically the start, growth, and cut-off of oil sprays from injection valves has been developed at the Langley Memorial Aeronautical Laboratory. The apparatus consists of a high-tension transformer by means of which a bank of condensers is charged to a high voltage. The controlled discharge of these condensers in sequence, at a rate of several thousand per second, produces electric sparks of sufficient intensity to illuminate the moving spray for photographing. The sprays are injected from various types of valves into a chamber containing gases at pressures up to 600 pounds per square inch. Several series of pictures are shown. The results give the effects of injection pressure, chamber pressure, specific gravity of the fuel oil used, and injection-valve design, upon spray characteristics.
    Type: NACA-TR-274
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  • 95
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    The relative performance obtained with several methods of control of an overcompressed engine using gasoline (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents some results obtained during an investigation to determine the relative characteristics for several methods of control of an overcompressed engine using gasoline and operating under sea-level conditions. For this work, a special single cylinder test engine, 5-inch bore by 7-inch stroke, and designed for ready adjustment of compression ratio, valve timing and valve lift while running, was used. This engine has been fully described in NACA-TR-250. Tests were made at an engine speed of 1,400 R. P. M. for compression ratios ranging from 4.0 to 7.6. The air-fuel ratios were on the rich side of the chemically correct mixture and were approximately those giving maximum power. When using plain domestic gasoline, detonation was controlled to a constant, predetermined amount (audible), such as would be permissible for continuous operation, by (a) throttling the carburetor, (b) maintaining full throttle but greatly retarding the ignition, and (c) varying the timing of the inlet valve to reduce the effective compression ratio. From the results of the tests, it may be concluded that method (b) gives the best all-round performance and, being easily employed in service, appears to be the most practicable method for controlling an overcompressed engine using gasoline at low altitudes.
    Type: NACA-TR-272
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  • 96
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    Pressure Distribution Tests on PW-9 Wing Models Showing Effects of Biplane Interference (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report tests are described in which the distribution of pressures over models of the wings of the PW-9 Airplane was investigated. The wing models were tested individually and in the biplane combination. The investigation was conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. It is concluded in this paper that the effect of biplane interference on the pressures on the wings is practically confined to the lower surface of the upper wing and the upper surface of the lower wing; that the overhanging portion of the upper wing is not greatly affected by the presence of the lower wing; and that a slight washing at the center section of the upper wing satisfactorily compensates for a reduced chord at this section (providing the airfoil section is not mutilated) and prevents a large reduction in the normal force over this portion of the wing.
    Type: NACA-TR-271
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  • 97
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    A Full-Scale Investigation of Ground Effect (1928)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: This report describes flight tests which were made with the Vought VE-7 airplane to determine the effects of flying close to the ground. It is found that the drag of an airplane is materially reduced upon approaching the ground and that the reduction may be satisfactorily calculated according to theoretical formulas. Several aspects of ground effect which have had much discussion are explained.
    Type: NACA-TR-265
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  • 98
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    Drag of wings with end plates (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report a formula for calculating the induced drag of multiplanes with end plates is derived. The frictional drag of the end plates are used, is sufficiently large to increase the efficiency of the wing. Curves showing the reduction of drag for monoplanes and biplanes are constructed; the influence of gap-chord ratio, aspect ratio, and height of end plate are determined for typical cases. The method of obtaining the reduction of drag for a multiplane is described. Comparisons are made of calculated and experimental results obtained in wind tunnel tests with airfoils of various aspect ratios and end plates of various sizes. The agreement between calculated and experimental results is good. Analysis of the experimental results shows that the shape and section of the end plates are important.
    Type: NACA-TR-267
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  • 99
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    The Effect of a Flap and Ailerons on the N.A.C.A. M-6 Airfoil Section (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the results obtained at the Langley Memorial Aeronautical Laboratory on an N. A. C. A. M-6 airfoil, fitted with a flap and ailerons, and tested in the variable density wind tunnel at a density of 20 atmospheres. Airfoil characteristics are given for the model up to 48 degree angle of attack with the flap set at various angles, and also with the ailerons set at similar angles. The approximate lift distribution and the center of pressure variation along the span are determined with the model at 18 degree angle of attack and with the ailerons displaced at 20 degrees. Approximate rolling moment and yawing moment coefficients are determined for the various aileron settings. A comparison of the calculated angles of zero lift and the calculated lift and moment coefficiencies with those observed is given in the appendix.
    Type: NACA-TR-260
    Format: application/pdf
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    Combustion time in the engine cylinder and its effect on engine performance (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a general program to study combustion in the engine cylinder and to correlate the phenomena of combustion with the observed performance of actual engines, this paper presents a sketchy outline of what may happen in the engine cylinder during the burning of a charge. It also suggests the type of information needed to supply the details of the picture and points out how combustion time and rate affect the performance of the engine. A theoretical concept of a flame front which is assumed to advance radially from the point of ignition is presented, and calculations based on the area and velocity of this flame and the density of the unburned gases are made to determine the mass rate of combustion. From this rate the mass which has been burned and the pressure at any instant during combustion are computed. This process is then reversed in an effort to determine actual rates of combustion and flame velocities from the pressures as recorded on indicator diagrams. The effects of different rates of combustion on engine performance are then discussed and the importance of proper spark advance is emphasized.
    Type: NACA-TR-276
    Format: application/pdf
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