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  • 1
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    Mechanism of faulting in Southern California indicated by seismograms (1941)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 31, no. 6, pp. 263-302, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Tectonics ; Seismicity ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Changes in sea-level, postglacial uplift, and mobility of the earth's interior (1941)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 52, no. 6, pp. 721-772, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Tectonics ; Gravimetry, Gravitation ; Fluids
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Notes of interest (roots of mountains) (1941)
    In:  Earthquake Notes, Milano, Gustav Fischer, vol. 13, no. 6, pp. 4, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Gravimetry, Gravitation
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Atmospheric-pressure waves near Pasadena (1941)
    In:  Trans., Am. Geophys. Union, Milano, Gustav Fischer, vol. 22, no. 6, pp. 424-426, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Waves ; NOISE ; Meteorology ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Travel times of principal P and S phases over small distances in Southern California (1944)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 34, no. 6, pp. 13-32, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Travel time ; Waves ; P-waves ; Shear waves ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    A method for the solution of certain non-linear problems in least squares (1944)
    In:  Quarterly Appl. Math., Luxembourg, Conseil de l'Europe, vol. 2, no. 22, pp. 164-168, pp. B02405, (ISSN: 1340-4202)
    Details
    Publication Date: 1944
    Keywords: Inversion
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    General theory of three-dimensional consolidation (1941)
    In:  J. Appl. Phys., Warszawa, Elsevier, vol. 12, no. 2, pp. 155-164, pp. L02307, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1941
    Keywords: Fluids ; Three dimensional ; sedimentation ; diagenesis ; Elasticity ; pores
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Seismology (1941)
    Geological Society of America
    In:  Professional Paper, Geology 1888-1938, 50th Anniversary Volume, New York, Geological Society of America, vol. 3, no. VIIa, pp. 438-470, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1941
    Keywords: Review article ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Reflected and minor phases in records of near-by earthquakes in Southern California (1944)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 34, no. 6, pp. 137-160, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Reflectivity ; Nearfield ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Larger shocks of 1942 (deep focus excluded) (1944)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1942, no. 6, pp. 115, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Frequency of earthquakes in California (1944)
    In:  Bull. Seism. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 34, no. 6, pp. 185-188, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Mechanism of faulting in Southern California indicated by seismograms (1941)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 52, no. 6, pp. 1950, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Tectonics ; Seismicity ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Tectonic processes now in action (1941)
    In:  Trans., Am. Geophys. Union, Milano, Gustav Fischer, vol. 22, no. 6, pp. 556-558, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Tectonics ; Seismicity ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Energy ratio of reflected and refracted seismic waves (1944)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 34, no. 6, pp. 85-102, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Reflectivity ; Energy (of earthquakes) ; Refraction seismics ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Larger shocks of 1941 (deep focus excluded) (1944)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1941, no. 6, pp. 98, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Larger shocks of 1943 (1944)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1943, no. 6, pp. 140, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    Reichspflanzenschutzblatt (1944)
    In:  Zeitschrift
    Details
    Publication Date: 1944
    Description: Detailierte Berichte über das Auftreten von Schaderregern in der Landwirtschaft für jedes Jahr; Zusammenhänge zu Witterungsbedingungen werden zu Beginn der entsprechenden Hefte, sowie teilw. bei Besprechung der jeweiligen Schaderreger hergestellt KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, regional aufgelöst ; 1944-1945 ; Pflanzenkrankheit ; Pflanzenschädling
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  • 18
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    Die Beziehungen zwischen dem Lebensraum und Lebensäußerungen von Insekten (1944)
    In:  Anz. Schädl.kunde 20: 16ff
    Details
    Publication Date: 1944
    Description: Beziehung zwischen Klima und Insektenbiologie KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, teilw. einzelne Regionen ; 1936-1941 ; Insekten ; Luftfeuchte ; Forst ; Klima ; Niederschlag ; Pflanzenschädling ; Temperatur
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  • 19
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    Zur Biologie von Dendrolimus pini L. (Lep., Lasiocampidae) (1944)
    In:  Ann. ent. fenn. 10: 181-183
    Details
    Publication Date: 1944
    Description: Beschreibung des Überwinterungsverhaltens des Kiefernspinners KATASTER-BESCHREIBUNG: Zusammenhang zwischen geografischer Breite, Temperatur und dem Überwinterungsverhalten des Kiefernspinners KATASTER-DETAIL: Delta T-, dann zweimaliges Überwintern der Larven bei Versuchen in Finnland
    Keywords: Finnland ; 1940-44 ; Insekten ; Kiefer ; Pflanzenschädling ; Temperatur
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  • 20
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    Die Massenvermehrung des Kiefernspanners, Bupalus piniarius L., und seine Bekämpfung im Jahre 1940 in der Westslowakei (1941)
    In:  Centralbl. ges. Forstwes. 67: 25-46, 53-59
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    Publication Date: 1941
    Keywords: Westslowakei ; 1940
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  • 21
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    Zur Prognose des Schadauftretens der Kiefernbuschhornblattwespe (Diprion pini L.) (1941)
    In:  Ztschr. Forst-, Jagdwesen 73: 201-246
    Details
    Publication Date: 1941
    Description: Beschreibung des Zusammenhangs zwischen der Eizahl und der Kokonzahl der Kiefernhornblattwespe auf das Massenauftreten KATASTER-BESCHREIBUNG: Betimmung der kritischen Anzhal Eier und der kritischen Anzahl Winter- und Sommerkokons für das Massenauftreten KATASTER-DETAIL:
    Keywords: Sachsen, Brandenburg, Mecklenburg-Vorpommern ; 1939-40 ; Insekten ; Kiefer ; Pflanzenschädling
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  • 22
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    Die Übervermehrung von Diprion pini L. im westslowakischen Kieferngebiet (1941)
    In:  Ztschr. Pfl.krankh. 51: 257-278
    Details
    Publication Date: 1941
    Description: Beschreibung der Massenvermehrung der Kiefernblattwespe, Hauptgrung ist die Umwandlung von ursprünglich Laubwaldgesellschaften in reine Kieferngesellschaften, Bedeutung der Temperatur für das Überliegen der Larven KATASTER-BESCHREIBUNG: Temperatur und Luftfeuchte für das Überliegen der Larven entscheidend und damit auch für ein Massenauftreten im darauffolgenden Jahr, Begünstigung der Parasitierung der Kieferblattwespe KATASTER-DETAIL: Delta T- (Juli-August und im Winter), dann Geschlechterfolge von Diprion pini stark dezimiert
    Keywords: Slowakei ; 1939-40 ; Insekten ; Luftfeuchte ; Kiefer ; Pflanzenschädling ; Temperatur ; Parasit
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  • 23
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    Zur Biologie des Forstschädlings Acantholyda erythrocephala L. (1941)
    In:  Photographie u. Forsch. 3: 161-169
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    Publication Date: 1941
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  • 24
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    Der Überwinterungsfraß der Tannenborkenkäfer. [Cryphalus picae] (1941)
    In:  Ztschr. angew. Ent. 28: 374-387
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    Publication Date: 1941
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  • 25
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    Zur Kenntnis der Kiefernschonungs-Gespinstblattwespe (Acantholyda erythrocephala L.) (1941)
    In:  Ztschr. angew. Ent. 28: 125-156
    Details
    Publication Date: 1941
    Description: Beschreibung von Massenauftreten mit wirtschaftlichem Schaden der Kiefernschonungs-Gespinstblattwespe (Acantholyda erythrocephala L.) in Europa, detaillierte Untersuchungen zum Massenauftreten östlich von Schwerin in den Jahren 1937-40 KATASTER-BESCHREIBUNG: Starker Anstieg des Befalls mit der Kiefernschonungs-Gespinstblattwespe in den Jahren 1939 und 1940, wirtschafltiche Schäden durch Absterben der Kiefern lagen bei 5% des Bestandes in einzelnen Unterförstereien KATASTER-DETAIL:
    Keywords: Mecklenburg-Vorpommern ; 1828-1940 ; Kiefer ; Pflanzenschädling
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  • 26
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    Weitere Beobachtungen zur Lebensweise der Kiefernschonungs-Gespinstblattwespe, Acantholyda erythrocephala L. (1944)
    In:  Ztschr. angew. Ent. 30: 364-371
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    Publication Date: 1944
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  • 27
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    Das Schadauftreten der Kiefernbuschhornblattwespe in Norddeutschland 1939/40. - Prognose und Verlauf der Massenvermehrung. (1941)
    In:  Vortrag Tagung Gr. Preußen - Mark Brdbg. Dtsch. Forstver. 27. 5:15-26, Fürstenwalde/Spree
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    Publication Date: 1941
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  • 28
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    Über das Auftreten und die Bekämpfung der Kiefernschonungs-Gespinstblattwespe (Acantholyda erythrocephala L.) im Forleulen-Aufforstungsgebiet des Netze-Warthe-Raumes in den Jahren 1937-1943 nebst grundsätzlichen Bemerkungen zur Entwicklung und wirtschaftlichen Behandlung der dortigen Waldflächen (1944)
    In:  Ztschr. ges. Forstwes. 76/70:87-97
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    Publication Date: 1944
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  • 29
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    Bekämpfung und Prognose der Kiefernschonungs-Gespinstblattwespe, Acantholyda erythrocephala L. (1941)
    In:  Forstarchiv 17: 57-61
    Details
    Publication Date: 1941
    Description: Beobachtungen über das vermehrte Auftreten der Kiefernschonungs-Gespinstblattwespe KATASTER-BESCHREIBUNG: Durch Massenvermehrung der Kiefernschonungs-Gespinstblattwespe und Fraß an Nadeln des Maitriebes bei Kieferen kommt es zum Absterben der Bäume, vorwiegend auf Kuppen und sandigen Standorten, weniger in Mulden und Senken KATASTER-DETAIL: Massenauftreten der Kiefernschonungs-Gespinstblattwespe führte bis 1939 zu Absterben von mindestens 5% der Kiefernbestände, nach 1940 noch höhere Schäden
    Keywords: Mecklenburg-Vorpommern ; 1920-40 ; Insekten ; Kiefer ; Pflanzenschädling
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  • 30
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    Weather and Winter drying (1941)
    In:  Plant Dis. Reptr. 25: 380-384
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    Publication Date: 1941
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  • 31
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    Frostwirkung an ostpreußischen Eichen von verschiedener Herkunft (1941)
    In:  Ztschr. Forst- u. Jagdwes. 73: 283-287
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    Publication Date: 1941
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  • 32
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    Zur Schädigung der Weißtanne durch Trieb- und Rindenläuse (Dryfusia) (1944)
    In:  Schweiz. Ztschr. Forstwes. 91: 201-209
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    Publication Date: 1944
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  • 33
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    Die Besiedlung künstlich geschwächter Bäume durch Insekten (1941)
    In:  Ztschr. angew. Ent. 28: 157-179
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    Publication Date: 1941
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  • 34
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    Neue forschungsergebnisse über holzzerstörende Insekten (1944)
    In:  Mitt. dtsch. Ges. Holzforschg. H. 34: 159-178
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    Publication Date: 1944
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  • 35
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    Untersuchungen zum Individualitätsproblem bei Forstinsekten (1941)
    In:  Mitt. Biol. Reichsanst. H. 63: 46-48
    Details
    Publication Date: 1941
    Description: Beschreibungen zum Gesundheitszustand einer Population von Nonnen, ihrer Lebens- und Vermehrungsfähigkeit im Zusammenhang mit dem Massenauftreten, aber auch dem Zusammenbrechen der Population KATASTER-BESCHREIBUNG: Verringerung der Populationssichte durch Räuber kann bei 95% liegen KATASTER-DETAIL:
    Keywords: Deutschland ; 1900-1940 ; Insekten ; Forst ; Pflanzenschädling
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  • 36
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    Ungewöhnliche Spätfrostschäden an Fichte und Kiefer (1944)
    In:  Forstwiss. Centralbl. Thar. forstl. Jahrb. 66: 115-120
    Details
    Publication Date: 1944
    Description: Beschreibung des Ertragsrückgang und der Schäden durch die Spätfröste im Mai 1943 KATASTER-BESCHREIBUNG: Spätfröste verursachten Schäden an Kiefern, Maitriebbildung teilweise extrem gestört und Posthorn- oder kandelaberartige Triebbildung als Folge des Frostes, unterschiedliche Empfindlichkeit der Baumarten KATASTER-DETAIL: Delta T -, (Ende Mai 〈 -6°C), dann schwere Schäden an Walnuss, Eiche, Robinie, Roteiche, Esche, Tanne, mittlere Schiiden:Buche, Roterle, Ahorn, Fichte, Douglasie, Lärche; geringe Schiiden: Roflkastanie,Hainbuche, Linde, Weisserle, Ulme, Birke. Im allgemeinen blieben ohne Schäden: Aspe, Eberesche, Traubenkirsche, Kiefer, Strobe und Bankskiefer.
    Keywords: Nordostdeutschland ; 1943 ; Buche ; Eiche ; Ertrag ; Fichte ; Forst ; Kiefer ; Roterle ; Frost ; Ulme ; Rosskastanie
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  • 37
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    Massenvermehrung forstlicher Schadinsekten (1941)
    In:  Dtsch. Forstztg. 10: 307-308
    Details
    Publication Date: 1941
    Description: Beschreibung der großen Frassschäden der letzten Jahrzehnte, bezug der Temperatur und des Niederschlages auf die Entwicklungsmöglichkeit einer Population KATASTER-BESCHREIBUNG: Ziiterte Untersuchungen zur Entwicklung der Nonnenraupe KATASTER-DETAIL: Delta T+ (Temperaturoptimum von 21.5°C, Ende April-Anfang Mai), dann günstige Entwiclungsbedingungen Delta Nied- (relative Feuchte schwankt zwischen 50-100%), dann Absterben großer Zahl futtersuchender Raupen
    Keywords: Deutschland, teilw. einzelne Regionen ; 1850-1940 ; Insekten ; Luftfeuchte ; Fichte ; Forst ; Kiefer ; Niederschlag ; Pflanzenschädling ; Temperatur
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  • 38
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    Zur Prognose von Nonnenvermehrungen (1941)
    In:  Mitt. Forstwirtsch. u. -wissensch. 12: 25-68
    Details
    Publication Date: 1941
    Description: Auswertung verschiedener Parameter (Nonnenraupen, Falterflug) in unterschiedlichen Überwachungsbereichen der Forstentomologischen Dienststellen, Befallsermittlungsverfahren nach der Wellensteinschen Methode KATASTER-BESCHREIBUNG: Rhytmische Schwankungen der plötzlichen Übervermehrung, 10 oder 12 jährige Perioden, Bezug zu Schwankungen der Umweltbedingungen KATASTER-DETAIL:
    Keywords: Nord- und Mitteldeutschland ; 1939-40 ; Insekten ; Fichte ; Forst ; Kiefer ; Pflanzenschädling
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  • 39
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    Agrilus ater L. als Espenschädling in Finnland (1941)
    In:  Ztschr. angew. Ent. 28: 357-365
    Details
    Publication Date: 1941
    Description: Vertrocknungsprozess der Espe, Beschreibung und Beziehung verschiedener Insekten und Pilze an diesem Prozess KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Finnland ; 1936-1941 ; Insekten ; Forst ; Pflanzenschädling
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  • 40
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    Zur Lebensweise des Agrilus sexguttatus Brahm (Col. Buprest.) (1944)
    In:  Anz. Schädl.kunde 20: 13-16
    Details
    Publication Date: 1944
    Description: Beschreibung zum Befall von kanadischen Pappeln mit dem Prachtkäfer KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Rheinland-Pfalz ; 1934-1943 ; Insekten ; Forst ; Pflanzenschädling
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  • 41
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    Seismicity of the earth (1941)
    Geol. Soc. Am.
    In:  New York, 7 + 131 pp., Geol. Soc. Am., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Seismicity ; Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 42
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    A Treatise on the Mathematical Theory of Elasticity (1944)
    Dover Publ.
    In:  New York, Dover Publ., vol. 5, no. 22, pp. 662-664, (ISBN 0-470-87000-1 (HB), ISBN 0-470-87001-X (PB))
    Details
    Publication Date: 1944
    Keywords: Textbook of geophysics ; Elasticity ; Dislocation
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    BIBLIOGRAPHY SEISMOLOGY
  • 43
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    A contribution to the seismic history of Missouri (1941)
    In:  Bull. Seism. Soc. Am., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 31, no. 19, pp. 187-224, pp. 1484, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 44
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    KEEPING AMERICA FIRST IN THE AIR (1944)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Keywords: BIOSCIENCES
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    NASA TECHNICAL REPORTS
  • 45
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    Summary of investigations undertaken at langley memorial aeronautical laboratory on problem of aircraft icing (1941)
    In:  Other Sources
    Details
    Publication Date: 2011-08-10
    Keywords: unknown
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  • 46
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    The Development of a New Lateral-Control Arrangement (1941)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Development work on an arrangement using ailerons and spoilers for lateral control was carried out by the Vought-Sikorsky Aircraft Division of the United Aircraft Corporation on a small commercial airplane in flight and on an airfoil in a wind tunnel. Spoiler hinge moments were reduced by aerodynamic balance. The arrangement was then built into an experimental airplane and further improvements were adopted as the result of flight and tunnel tests. The use of ailerons for lateral control with flaps up, spoilers with flaps full down, and gradual transition as the flaps are lowered was found to provide lateral control under the flight conditions for which they were best suited. The ailerons were of short span, permitting the use of long-span flaps, and were drooped to a relatively large angle when the flaps were deflected. A high maximum lift coefficient was thus attained. With large control deflections in the intermediate flap-angle range and spoiler effectiveness near neutral improved by "ventilating" the spoiler, the lateral control was satisfactory for the experimental airplane and was a definite improvement over that of a conventional control arrangement.
    Keywords: Aircraft Design, Testing and Performance
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  • 47
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    A Theoretical Investigation of Longitudinal Stability of Airplanes with Free Controls Including Effect of Friction in Control System (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The relation between the elevator hinge moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance. The stability of the short period oscillations is shown as a series of boundaries giving the limits of the stable regions in terms of the elevator hinge moment parameters. The effects of static stability, elevator moment of inertia, elevator mass unbalance, and airplane density are also considered. Dynamic instability is likely to occur if there is mass unbalance of the elevator control system combined with a small restoring tendency (high aerodynamic balance). This instability can be prevented by a rearrangement of the unbalancing weights which, however, involves an increase of the amount of weight necessary. It can also be prevented by the addition of viscous friction to the elevator control system provided the airplane center of gravity is not behind a certain critical position. For high values of the density parameter, which correspond to high altitudes of flight, the addition of moderate amounts of viscous friction may be destabilizing even when the airplane is statically stable. In this case, increasing the viscous friction makes the oscillation stable again. The condition in which viscous friction causes dynamic instability of a statically stable airplane is limited to a definite range of hinge moment parameters. It is shown that, when viscous friction causes increasing oscillations, solid friction will produce steady oscillations having an amplitude proportional to the amount of friction.
    Keywords: Aircraft Stability and Control
    Type: AD-A301267 , NACA-TR-791
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  • 48
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    Model tests of a wing-duct system for auxiliary air supply (1941)
    In:  CASI
    Details
    Publication Date: 2019-05-31
    Keywords: unknown
    Type: NASA-TM-X-57675 , NACA-SR-175
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  • 49
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    Simply supported long rectangular plate under combined axial load and normal pressure (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-949
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  • 50
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    Stresses at Cut-outs in Shear Resistant Webs as Determined by the Photoelastic Method (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-984
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  • 51
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    Guides for preventing buckling in axial fatigue tests of thin sheet-metal specimens (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-931
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  • 52
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    Wind-tunnel Investigation of the Effect of Vertical Position of the Wing on the Side Flow in the Region of the Vertical Tail (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-804
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  • 53
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    Normal pressure tests on unstiffened flat plates (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flat sheet panels of aluminum alloy (all 17S-T except for two specimens of 24S-T) were tested under normal pressures with clamped edge supports in the structures laboratory of the Guggenheim Aeronautical Laboratory, California Institute of Technology. The thicknesses used ranged from 0.010 to 0.080 inch; the panel sizes ranged from 10 by 10 inches to 10 by 40 inches; and the pressure range was from 0 to 60-pounds-per-square-inch gage. Deflection patterns were measured and maximum tensile strains in the center of the panel were determined by electric strain gages. The experimental data are presented by pressure-strain, pressure-maximum-deflection, and pressure-deflection curves. The results of these tests have been compared with the corresponding strains and deflections as calculated by the simple membrane theory and by large deflection theories.
    Type: NACA-TN-943
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  • 54
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    The numerical solution of compressible fluid flow problems (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerical methods have been developed for obtaining the steady, adiabatic flow field of a frictionless, perfect gas about arbitrary two-dimensional bodies. The solutions include the subsonic velocity regions, the supersonic velocity regions, and the transition compression shocks, if required. Furthermore, the rotational motion and entropy changes following shocks are taken into account. Extensive use is made of the relaxation method. In this report the details of the methods of solution are emphasized so as to permit others to solve similar problems. Solutions already obtained are mentioned only by way of illustrating the possibilities of the methods described. The methods can be applied directly to wind tunnel and free air tests of arbitrary airfoil shapes at subsonic, sonic, and supersonic speeds.
    Type: NACA-TN-932
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  • 55
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    The inward bulge type buckling of monocoque cylinders I : calculation of the effect upon the buckling stress of a compressive force, a nonlinear direct stress distribution, and a shear force (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present part I of a series of reports on the inward bulge type buckling of monocoque cylinders the buckling load in combined bending and compression is first derived. Next the reduction in the buckling load because of a nonlinear direct stress distribution is determined. In experiments nonlinearity may result from an inadequate stiffness of the end attachments in actual airplanes from the existence of concentrated loads or cut-outs. The effect of a shearing force upon the critical load is investigated through an analysis of the results of tests carried out at GALCIT with 55 reinforced monocoque cylinders. Finally, a simple criterion of general instability is presented in the form of a buckling inequality which should be helpful to the designer of a monocoque in determining the sizes of the rings required for excluding the possibility of inward bulge type buckling.
    Type: NACA-TN-938
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  • 56
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    Analysis of square shear web above buckling load (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A solution of Von Karman's fundamental equations for plates with large deflections is presented for the case of a shear web divided into square panels by reinforcing struts. Numerical solutions are given for struts of infinite rigidity and for struts the weight of which is one-fourth the weight of the sheet. The results are compared with Wagner's diagonal tension theory as extended by Kuhn and by Langhaar. It is found that the diagonal tension theory as developed by Kuhn agrees best with the present paper in the practical range when r=1/4. Kuhn's theory is in especially good agreement for the force in the strut when r=1/4.
    Type: NACA-TN-962
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  • 57
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    The aerodynamics of a wind-tunnel fan (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The vortex blade-element theory modified to apply to an axial fan working in a duct is reviewed. Thrust and power coefficients for a fan are identified with the corresponding coefficients for airplane propellers. The relation of pressure produced by the fan to the blade-element coefficients is developed. The distribution of axial velocity of fluid through a fan is assumed to be controlled by the fan itself. The radial distribution of tangential velocity imported by the fan to fluid moving through the fan is shown to be independent of the axial-velocity distribution. A nondimensional coefficient, designated the rotation constant, is introduced. This constant is based solely upon design information. The use of the rotation constant in simplifying the design of a fan for a specific operating condition is demonstrated. Based on the use of the rotation constant, a graphical method is outlined by which the performance of a given fan in a given wind tunnel may be predicted and by which the distributions of axial velocity of the fluid through the fan under various operating conditions may be established.
    Type: NACA-TN-820
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  • 58
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    Wind-tunnel investigation of an NACA 23012 airfoil with several arrangements of slotted flaps with extended lips (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip location on the aerodynamic section characteristics of an NACA 23012 airfoil with a 30-percent-chord slotted flap. Tests were made with slot lips located at 90 and 100 percent of the airfoil chord and with two different flap shapes. The results are compared with a slotted flap previously developed by the National advisory Committee for Aeronautics with a slot lip located at 83 percent of the airfoil chord. The extension of the slot lip to the rear increased the section lift and pitching-moment coefficients. Comparisons made on a basis of pitching moment for a given tail length show that the Fowler type flap, lip extended to trailing edge of the airfoil, has the greatest section lift coefficient. For moderate tail lengths, 2 to 3 chord lengths, there was only a slight difference between the previously developed slotted flap and the slotted flap with slot lip extended to 90 percent of the airfoil chord. Of the three flaps tested, the Fowler flap had the lowest drag coefficient at high lift coefficients. The extension of the lower surface at the leading edge of the slot had a negligible effect on the profile drag of the airfoil-flap arrangement with the flap deflected when the lip terminated at 90 percent of the airfoil chord.
    Type: NACA-TN-808
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  • 59
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    Correction of the lifting-line theory for the effect of the chord (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is shown that a simple correction for the chord of a finite wing can be deduced from the three-dimensional potential flow around an elliptic plate. When this flow is compared with the flow around a section of an endless plate, it is found that the edge velocity is reduced by the factor 1/E, where E is the ratio of the semiperimeter to the span. Applying this correction to the circulation brings the theoretical lift into closer agreement with experiments.
    Type: NACA-TN-817
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  • 60
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    On the general theory of thin airfoils for nonuniform motion (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: General thin-airfoil theory for a compressible fluid is formulated as boundary problem for the velocity potential, without recourse to the theory of vortex motion. On the basis of this formulation the integral equation of lifting-surface theory for an incompressible fluid is derived with the chordwise component of the fluid velocity at the airfoil as the function to be determined. It is shown how by integration by parts this integral equation can be transformed into the Biot-Savart theorem. A clarification is gained regarding the use of principal value definitions for the integral which occur. The integral equation of lifting-surface theory is used a s the starting point for the establishment of a theory for the nonstationary airfoil which is a generalization of lifting-line theory for the stationary airfoil and which might be called "lifting-strip" theory. Explicit expressions are given for section lift and section moment in terms of the circulation function, which for any given wing deflection is to be determined from an integral equation which is of the type of the equation of lifting-line theory. The results obtained are for airfoils of uniform chord. They can be extended to tapered airfoils. One of the main uses of the results should be that they furnish a practical means for the analysis of the aerodynamic span effect in the problem of wing flutter. The range of applicability of "lifting-strip" theory is the same as that of lifting-line theory so that its results may be applied to airfoils with aspect ratios as low as three.
    Type: NACA-TN-946
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  • 61
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    The inward bulge type buckling of monocoque cylinders II : experimental investigation of the buckling in combined bending and compression (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the second part of a series of reports on the inward bulge type buckling of monocoque cylinders. It presents the results of an experimental investigation of buckling in combined bending and compression. In the investigation it was found that the theory developed in part I of the present series predicts the buckling load in combined bending and compression with the same degree of accuracy as the older theory does in pure bending. In the realm covered by the experiments no systematic variation of the parameter N was observed. The analysis of the test results afforded a check on the theories of buckling of a curved panel. The agreement between experiment and theory was reasonably good. In addition, the effect of the end conditions upon the stress distribution under loads and upon initial stresses was investigated.
    Type: NACA-TN-939
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  • 62
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    The "limiting line" in mixed subsonic and supersonic flow of compressible fluids (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is well known that the vorticity for any fluid element is constant if the fluid is non-viscous and the change of state of the fluid is isentropic. When a solid body is placed in a uniform stream, the flow far ahead of the body is irrotational. Then if the flow is further assumed to be isentropic, the vorticity will be zero over the whole filed of flow. In other words, the flow is irrotational. For such flow over a solid body, it is shown by Theodorsen that the solid body experiences no resistance. If the fluid has a small viscosity, its effect will be limited in the boundary layer over the solid body and the body will have a drag due to the skin friction. This type of essentially isentropic irrotational flow is generally observed for a streamlined body placed in a uniform stream, if the velocity of the stream is kept below the so-called "critical speed." At the critical speed or rather at a certain value of the ratio of the velocity of the undisturbed flow and the corresponding velocity of sound, shock waves appear. This phenomenon is called the "compressibility bubble." Along a shock wave, the change of state of the fluid is no longer isentropic, although still adiabatic. This results in an increase in entropy of the fluid and generally introduces vorticity in an originally irrotational flow. The increase in entropy of the fluid is, of course, the consequence of changing part of the mechanical energy into heat energy. In other words, the part of fluid affected by the shock wave has a reduced mechanical energy. Therefore, with the appearance of shock waves, the wake of the streamline body is very much widened, and the drag increases drastically. Furthermore, the accompanying change in the pressure distribution over the body changes the aerodynamic moment acting on it and in the case of an airfoil decreases the lift force. All these consequences of the breakdown of isentropic irrotational flow are generally undesirable in applied aerodynamics. Its occurrence should be delayed as much as possible by modifying the shape or contour of the body. However, such endeavor will be very much facilitated if the cause or the criterion for the breakdown can be found first.
    Type: NACA-TN-961
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  • 63
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    Dynamics of the inlet system of a four-stroke engine (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were run on a single-cylinder and a multicylinder four-stroke engine in order to determine the effect of the dynamics of the inlet system upon indicated mean effective pressure. Tests on the single-cylinder engine were made at various speeds, inlet valve timings, and inlet pipe lengths. These tests indicated that the indicated mean effective pressure could be raised considerably at any one speed by the use of a suitably long inlet pipe. Tests at other speeds with this length of pipe showed higher indicated mean effective pressure than with a very short pipe, although not so high as could be obtained with the pipe length adjusted for each speed. A general relation was discovered between optimum time of inlet valve closing and pipe length; namely, that longer pipes require later inlet valve closing in order to be fully effective. Tests were also made on three cylinders connected to a single pipe. With this arrangement, increased volumetric efficiency at low speed was obtainable by using a long pipe, but only with a sacrifice of volumetric efficiency at high speed. Volumetric efficiency at high speed was progressively lower as the pipe length was increased.
    Type: NACA-TN-935
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  • 64
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    Axial Fatigue Tests at Zero Mean Stress of 24S-T Aluminum-alloy Sheet with and Without a Circular Hole (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Axial fatigue tests were made on 189 coupon specimens of 0.032-inch 24S-T aluminum-alloy sheet and a few supplementary specimens of 0.004-inch sheet. The mean load was zero. The specimens were restrained against lateral buckling by lubricated solid guides described in a previous report on this project. About two-thirds of the 0.032-inch specimens were plain coupons nominally free from stress raisers. The remainder contained a 0.1285-inch drilled hole at the center where the reduced section was 0.5 inch wide. S-N diagrams were obtained for cycles to failure between about 1000 and 10 to the 7th power cycles for the plain specimens and 17 and 10 to the 7th power cycles for the drilled specimens. The fatigue stress concentration factor increased from about 1.08 for a stress amplitude causing failure at 0.25 cycles (static) to a maximum of 1.83 at 15,000 cycles and then decreased gradually. The graph for the drilled specimens showed less scatter than that for the plain specimens.
    Type: NACA-TN-955
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  • 65
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    Notes on the Stability and Control of Tailless Airplanes (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback. With sweepback, a flap over the center section of the wing may be used to serve the dual purpose of elevator control and high-lift device. Sweepback introduces undesirable stalling characteristics, however, and may require auxiliary devices to prevent stalling of the tips.
    Keywords: Aerodynamics
    Type: NACA-TN-837
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  • 66
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    Determination of control-surface characteristics from NACA plain-flap and tab data (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The data from previous NACA pressure-distribution investigations of plain flaps and tabs have been analyzed and are presented in this paper in a form readily applicable to the problems of control-surface design. The experimentally determined variation of aerodynamic parameters with flap chord and tab chord are given in chart form and comparisons are made with the theory. With the aid of these charts and the theoretical relationships for a thin airfoil, the aerodynamic characteristics for control surfaces of any plan form with plain flaps and tabs may be determined. A discussion of the basic equations of the thin-airfoil theory and the development of a number of additional equations that will be helpful in tail design are presented in the appendixes. The procedure for applying the data is described and a sample problem of tail design is included. The data presented and the method of application set forth in this report should provide a reasonably accurate and satisfactory means of computing the aerodynamic characteristics of control surfaces.
    Type: NACA-TN-796
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  • 67
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    Damping characteristics of dashpots (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the damping characteristics of dashpots was carried out combining theory and experiment. Laminar flow was assumed and three equations for the steady velocity of a piston moving in a cylinder filled with liquid were derived. In the first equation, the piston was assumed coaxial in the cylinder and, in the second equation, the piston was assumed eccentric in the cylinder with an element of the piston in contact with the cylinder wall. The third equation is for a piston of circular cross section in an elliptical cylinder. Experiments showed that the piston is normally eccentric in the cylinder. The pistons tested were 1.25 and 2 inches in diameter 0.062 to 1.00 inch long, and the clearances varied from 1.36 to 5.16 x 10 to the 3rd power inch. The difference in pressure on the two sides of the piston varied from about 2 to 55 pounds per square inch. The piston velocities for each assembly were measured with damping liquids of three different viscosities. At high piston velocities, when turbulent flow exists, the observed velocities were much lower than the velocities calculated on the basis of laminar flow. Results for a wide range of Reynolds numbers are presented in graphical form.
    Type: NACA-TN-830
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  • 68
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    Data on Material Properties and Panel Compressive Strength of a Plastic-bonded Material of Glass Cloth and Canvas (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented of tests for determining the tensile, compressive, and bending properties of a material of plastic-bonding glass cloth and canvas layers. In addition, 10 panel specimens were tested in compression. Although the material is not satisfactory for primary structural use in aircraft when compared on a strength-weight basis with other materials in common use, there appears to be potential strength in the material that will require research for development. These points are considered in some detail in the concluding discussion of the report. An appendix shows that a higher tensile strength can be obtained by changes in the type of weave used in the glass-cloth reinforcement.
    Type: NACA-TN-975
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  • 69
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    The Influence of the Aerodynamic Span Effect on the Magnitude of the Torsional-divergence Velocity and on the Shape of the Corresponding Deflection Mode (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A procedure which takes into account the aerodynamic span effect is given for the determination of the torsional-divergence velocities of monoplanes. The explicit solutions obtained in several cases indicate that the aerodynamic span effect may increase the divergence velocities found by means of the section-force theory by as much as 17 to 40 percent. It is found that the magnitude of the effect increases with increasing degree of stiffness taper and decreases with increasing degree of chord taper. By a slight extension of the present method it is possible to analyze the elastic deformations of wings, and the resultant lift distributions, before torsional divergence occurs.
    Type: NACA-TN-926
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  • 70
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    Some Comparative Tests of Plain and Alclad 24S-T Sheet (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-821
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  • 71
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    The tensile elastic properties at low temperatures of 18:8 Cr-Ni steel as affected by heat treatment and slight plastic deformation (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-818
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  • 72
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    The Design of Jet Pumps (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report shows that by applying both energy and impulse theorems the optimum throat dimension of the mixing nozzle and the best shape of intake can be predicted approximately in a relatively simple manner. The necessary length of the mixing nozzle follows from Prandtl's turbulent mixing theory. The calculations are carried out for the mixing of similar and dissimilar fluids.
    Type: NACA-TM-982
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  • 73
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    Factors Influencing the Fatigue Strength of Materials (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A number of factors are considered which influence the static and fatigue strength of materials under practical operating conditions as contrasted with the relations obtaining under conditions of the usual testing procedure. Such factors are interruptions in operation, periodically fluctuating stress limits and mean stresses with periodic succession of several groups and stress states, statistical changes and succession of stress limits and mean stresses, frictional corrosion at junctures, and notch effects.
    Type: NACA-TM-987
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  • 74
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    Researches on direct injection in internal-combustion engines (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These researches present a solution for reducing the fatigue of the Diesel engine by permitting the preservation of its components and, at the same time, raising its specific horsepower to a par with that of carburetor engines, while maintaining for the Diesel engine its perogative of burning heavy fuel under optimum economical conditions. The feeding of Diesel engines by injection pumps actuated by engine compression achieves the required high speeds of injection readily and permits rigorous control of the combustible charge introduced into each cylinder and of the peak pressure in the resultant cycle.
    Type: NACA-TM-993
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  • 75
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    The Creep of Laminated Synthetic Resin Plastics (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The long-time loading strength of a number of laminated synthetic resin plastics was ascertained and the effect of molding pressure and resin content determined. The best value was observed with a 30 to 40 percent resin content. The long-time loading strength also increases with increasing molding pressure up to 250 kg/cm(exp 2); a further rise in pressure affords no further substantial improvement. The creep strength is defined as the load which in the hundredth hour of loading produces a rate of elongation of 5 X 10(exp -4) percent per hour. The creep strength values of different materials were determined and tabulated. The effect of humidity during long-term tests is pointed out.
    Type: NACA-TM-995
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  • 76
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    Inertia of dynamic pressure arrays (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From earlier measurements and the mathematical examples, it can be gathered that the inertia of dynamic pressure arrays can be computed with sufficient accuracy and the proper size of tubing established, provided that certain requirements are made on the inertia.
    Type: NACA-TM-998
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  • 77
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    Stress Analysis of Circular Frames (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stresses in circular frames of constant bending stiffnesses, as encountered in thin-wall shells, are investigated from the point of view of finite depth of sectional area of frame. The solution is carried out for four fundamental load conditions. The method is illustrated on a worked out example.
    Keywords: Structural Mechanics
    Type: NACA-TM-999
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  • 78
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    General airfoil theory (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: On the assumption of infinitely small disturbances the author develops a generalized integral equation of airfoil theory which is applicable to any motion and compressible fluid. Successive specializations yield various simpler integral equations, such as Possio's, Birnbaum's, and Prandtl's integral equations, as well as new ones for the wing of infinite span with periodic downwash distribution and for the oscillating wing with high aspect ratio. Lastly, several solutions and methods for solving these integral equations are give.
    Type: NACA-TM-979
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  • 79
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    New frictional resistance law for smooth plates (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From measurements in the free boundary layer of a plate the laws governing the velocity distribution and a new resistance law are derived which, by increasing Reynolds number Re(sub x) afford lower resistance values than the logarithmic law. The transverse velocities, the shearing stress, and the mixing path profiles were also defined.
    Type: NACA-TM-986
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  • 80
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    Stagnation Temperature Recording (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report deals with the development of a thermometer for recording stagnation temperature in compressible mediums in turbulent flow within 1 to 2 percent error of the adiabatic temperature in the stagnation point, depending upon the speed. This was achieved by placing the junction of a thermocouple near the stagnation point of an aerodynamically beneficial body, special care being taken to assure an uninterrupted supply of fresh compressed air on the junction together with the use of metals of low thermal conductivity, thus keeping heat-transfer and heat-dissipation losses to a minimum. In other experiments the use of the plate thermometer was proved unsuitable for practical measurements by reason of its profound influence in the reading by the Reynolds number and by the direction of flow.
    Type: NACA-TM-967
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  • 81
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    Potential flow through centrifugal pumps and turbines (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The methods of conformal transformation up to the present have been applied to the potential flows in the rotation of solid bodies only to a limited extent. This report deals with aspects of centrifugal pumps and turbines such as: the complex potential for rotation, potential for the flow due to the blade rotation, velocities at the blade tip, comparison with "infinite number of blades," and a variable number of blades.
    Type: NACA-TM-973
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  • 82
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    Boundary layer removal by suction (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight-test data and wind-tunnel data on suction profiles are substantially in agreement. The lift values found in the model test can be actually flown and used as a basis for the design. To visualize the action of the suction, the flow conditions with and without suction on the upper surface were photographed; figures 12 to 15 are sections of the film.
    Type: NACA-TM-974
    Format: application/pdf
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  • 83
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    The oscillating wing with aerodynamically balanced elevator (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The two-dimensional problem of the oscillating wing with aerodynamically balanced elevator is treated in the manner that the wing is replaced by a plate with bends and stages and the airfoil section by a mean line consisting of one or more straights. The computed formulas and tables permit, on these premises, the prediction of the pressure distribution and of the aerodynamic reactions of oscillating elevators and tabs with any position of elevator hinge in respect to elevator leading edge.
    Type: NACA-TM-991
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  • 84
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    Experiences with Flow-direction Instruments (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The method of recording the direction of flows on the basis of the hydrodynamic zero-point measurement has now reached a certain limit, in spite of the good results achieved. While the available flow-direction devices are accurate enough for many purposes, they are all insufficient for perfectly exact prediction of the flow direction. The next problem will be to achieve a point-by point flow-direction record, whereby the test procedure must be simplified, accelerated, and the degree of accuracy of the test data improved.
    Type: NACA-TM-969
    Format: application/pdf
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  • 85
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    Use of charts for flow discharge calculations (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Various problems in connection with engine design involve flow-discharge calculations which are rendered difficult both on account of the large number of external variables that enter into the computation - i.e., changes in discharge area during the process, change in volume of the cylinder, pressure, etc., and changes in the thermal constants themselves of the flow medium. A fairly accurate solution that does not involve an excessive amount of labor can be obtained only through the extensive use of i-s tables. In the present report, a solution is offered in the form of a different method making use of the I-S table of Lutz and Wolf.
    Type: NACA-TM-972
    Format: application/pdf
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  • 86
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    Present and Future Problems of Airplane Propulsion (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some of the problems considered in this report include: thermodynamics of surface friction, application of thick wing sections, special applications of controllable propellers, and gas turbines for aircraft.
    Type: NACA-TM-976
    Format: application/pdf
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  • 87
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    Air Transport by Gliders : Some Technical Observations (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
    Type: NACA-TM-980
    Format: application/pdf
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  • 88
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    Integral methods in the theory of the boundary layer (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The application of the well-known basic principle of mechanics, the principle of Jourdain, to problems of the theory of the boundary layerleads tp an equation from which the equations of Von Karman, Leibenson, and Golubev are derived as special cases. The given equation may be employed in other integral methods. The present paper deals with the method of the variation of the thickness of the boundary layer. A number of new approximate formulas valuable in aerodynamic calculations for the fristion distribution are derived from this procedure. The method has been applied only to laminar boundary layers, but it seems probable that it may be generalized to include turbulent layers as well.
    Type: NACA-TM-1070
    Format: application/pdf
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  • 89
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    Protection of Nonmetallic Aircraft from Lightning III : Electrical Effects in Glider Towlines (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-W-62
    Format: application/pdf
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  • 90
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    Investigation of the Behavior of Parallel Two-Dimensional Air Jets (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made of the flow downstream from a "two-dimensional" grid formed of parallel rods. In both two and three dimensional jet fields there is a critical range of grid density below which the downstream flow is stable and above which it is unstable. The flow can be completely stabilized by means of an adequate lateral contraction beginning immediately after the grid or by use of a fine-mesh damping screen parallel to the grid plane and within a definite range of positions downstream from the grid.
    Keywords: Aerodynamics
    Type: NACA-WR-W-90 , NACA-ACR-4H24
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  • 91
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    Effect of hinge-moment parameters on elevator stick forces in rapid maneuvers (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-185 , NACA-ARR-L4J12
    Format: application/pdf
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  • 92
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    Internally finned honeycomb radiators (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-492
    Format: application/pdf
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  • 93
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    The Selection of Propellers for High Thrust at Low Airspeed (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problem of improving thrust at low speeds is primarily one of reducing angle of attack of operation of sections to improve L/D or reducing blade helix angle. An analysis, based on recent propeller data, is presented for determining improvements in thrust or efficiency which could be obtained by increased number of blades, increased blade width, increased diameter, dual rotation, and two-speed gearing. All methods were found very effective, particularly two-speed gearing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-483
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  • 94
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    Tests of the Northrop MX-334 Glider Airplane in the NACA Full-scale Tunnel (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-628
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  • 95
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    Ditching Tests with a 1/12-size Model of the Army B-26 Airplane in NACA Tank Number 2 and on an Outdoor Catapult (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-619
    Format: application/pdf
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  • 96
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    A Laboratory Investigation of Icing and Heated-air De-icing of a Chandler-evans 1900 CPB-3 Carburetor-mounted on a Pratt and Whitney R-1830-C4 Intermediate Rear Engine Section (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-E-15 , NACA-ARR-E4J03
    Format: application/pdf
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  • 97
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    An Investigation of the Characteristics of Alcohol-distribution Tubes Used for Ice Protection on Aircraft Windshields (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-A-20 , NACA-ARR-4B26
    Format: application/pdf
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  • 98
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-528 , NACA-ACR-L4D26
    Format: application/pdf
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  • 99
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    Study of Jet-Propulsion System Comprising Blower, Burner, and Nozzle (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of the performance of a jet-propulsion system composed of an engine-driven blower, a combustion chamber, and a discharge nozzle. A simplified analysis is made of this system for the purpose of showing in concise form the effect of the important design variables and operating conditions on jet thrust, thrust horsepower, and fuel consumption. Curves are presented that permit a rapid evaluation of the performance of this system for a range of operating conditions. The performance for an illustrative case of a power plant of the type under consideration id discussed in detail. It is shown that for a given airplane velocity the jet thrust horsepower depends mainly on the blower power and the amount of fuel burned in the jet; the higher the thrust horsepower is for a given blower power, the higher the fuel consumption per thrust horsepower. Within limits the amount of air pumped has only a secondary effect on the thrust horsepower and efficiency. A lower limit on air flow for a given fuel flow occurs where the combustion-chamber temperature becomes excessive on the basis of the strength of the structure. As the air-flow rate is increased, an upper limit is reached where, for a given blower power, fuel-flow rate, and combustion-chamber size, further increase in air flow causes a decrease in power and efficiency. This decrease in power is caused by excessive velocity through the combustion chamber, attended by an excessive pressure drop caused by momentum changes occurring during combustion.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-212 , NACA-ACR-E4E06
    Format: application/pdf
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  • 100
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    Drag measurements of a protruding 0.50-caliber machine gun (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-348
    Format: application/pdf
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