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  • Other Sources  (337)
  • 1975-1979
  • 1935-1939  (337)
  • 1937  (185)
  • 1936  (152)
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  • 1975-1979
  • 1935-1939  (337)
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  • 1
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    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:5718 | KART H 86:5718
    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. GeoTIFF erstellt durch FID GEO, SUB Göttingen. Koordinaten Vorlage: E 008 40 - E 008 50 / N 050 18 - N 050 12
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Rodheim ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 64
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  • 2
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    In:  Geophysics, Milano, Gustav Fischer, vol. 1, no. 3, pp. 252-256, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Applied geophysics ; Amplitude ; Seismics (controlled source seismology)
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  • 3
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    In:  Beiträge zur angewandten Geophysik, Milano, Gustav Fischer, vol. 6, no. 3, pp. 125-140, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Applied geophysics ; Seismics (controlled source seismology)
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  • 4
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    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 47, no. 3, pp. 306-307, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Tectonics ; CRUST ; Earth model, also for more shallow analyses ! ; Plate tectonics
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  • 5
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    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 47, no. 3, pp. 73-131, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Waves ; Seismology ; Review article
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  • 6
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    In:  Science, Milano, Gustav Fischer, vol. 83, no. 3, pp. 183-185, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Seismology ; Magnitude ; Energy (of earthquakes)
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  • 7
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    In:  Geophysics, Milano, Gustav Fischer, vol. 2, no. 3, pp. 185-187, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Review article
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  • 8
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    In:  Petroleum Eng., Milano, Gustav Fischer, vol. 8, no. 6, pp. 78, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Review article
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  • 9
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 27, no. 6, pp. 337-348, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Travel time ; Velocity analysis ; Inhomogeneity ; Seismology ; BSSA
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  • 10
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 27, no. 6, pp. 157-184, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Seismology ; Hypocentral depth ; BSSA
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  • 11
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    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 27, no. 6, pp. 240, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Applied geophysics
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  • 12
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    In:  Physics, Luxembourg, Conseil de l'Europe, vol. 7, no. B4, pp. 195-202, pp. B04202, (ISSN: 1340-4202)
    Publication Date: 1936
    Keywords: Source ; Dislocation ; Elasticity
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  • 13
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    In:  Phil. Mag., Bonn, Pergamon, vol. 7, no. 2, pp. 1017-1032, pp. B05S04, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Elasticity ; temperature
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  • 14
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    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 46, no. 3, pp. 198-201, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Seismology ; mathematics ; geometry
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  • 15
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 26, no. 3, pp. 341-390, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Seismology ; Hypocentral depth ; BSSA
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  • 16
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    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 83, no. 3, pp. 341, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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  • 17
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    In:  The Sky, Milano, Gustav Fischer, vol. 2, no. 6, pp. 12-13, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Seismology ; Seismicity
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  • 18
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    In:  Petroleum World, Annual Review, Milano, Gustav Fischer, vol. 34, no. 6, pp. 12-13, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1937
    Keywords: Applied geophysics
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  • 19
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    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 26, no. 3, pp. 111-117, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Micro seismicity ; NOISE ; BSSA
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  • 20
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    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 47, no. 3, pp. 1587-1610, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1936
    Keywords: Tectonics ; CRUST ; Earth model, also for more shallow analyses ! ; Plate tectonics
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  • 21
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    In:  Prakt. Blätt. Pflanzenb. u. –schutz 14;p. 343-348
    Publication Date: 1937
    Description: Der Autor schildert detailliert den Witterungsverlauf des Vegetationsjahres 1935/36, gibt eine kleine Übersicht über die aufgetretenen Pflanzenkarankheiten und -schädlinge und bringt beides ansatzweise in einen Zusammenhang. Zudem listet er die Erträge des Vegetationsjahres auf und beurteilt diese. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bayern ; 1936 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Wachstum ; Witterung ; Hackfrüchte ; Hochwasser
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  • 22
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    In:  Die Gartenbauwissenschaft 10: 289-353
    Publication Date: 1937
    Description: Beschreibung der Beziehungen zwischen Ernteerträgen und der Witterung (Temperatur und Niederschlag mithilfe der Rangordungsmethode nach Holdefleiss) in 2 unterschiedlich klimatischen Regionen, Bestimmung von kritischen Zeiten, Auswirkungen auf die Obstsorten und -arten. KATASTER-BESCHREIBUNG: Faktoren Niederschlag und Temperatur haben zu bestimmten Zeiten wichtige Funktionen, schwanken aber zwischen den Arten und Sorten, jedoch Niederschlag ab Mai gewinnt umso mehr an Bedeutung, je geringer die Wasserspeicherkapazität des Bodens, höchster Wasserbedarf im Mai/Juni KATASTER-DETAIL: Delta Temp+ (April im Erntejahr), dann Ertrag ++ Delta Nied Juni (〉63mm Mittel von 1928-33 in Dahlem), dann Ertrag Gravensteiner 〉 115kg Delta Nied+ und Delta Temp+ (Juli-August im Vorjahr), dann Ertrag ++ Delta Nied- (Juli-August im aktuellen Jahr, , dann Ertrag -
    Keywords: Berlin, Hohenheim ; 1909-33, 1907-28 ; Apfel ; Ertrag ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Birne
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  • 23
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    In:  Zeitschrift für Pflanzenernährung, Düngung und Bodenkunde 2 (47): 127-166
    Publication Date: 1936
    Description: Auswertung von Lysimeter, Gefäß- und Versuchsstandorten, um Wasserverbrauch, aber auch Wasserhaltekapazität verschiedener Böden zu bestimmen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Berlin-Dahlem ; 1935
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  • 24
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    In:  Der Forschungsdienst 2: 581-587
    Publication Date: 1937
    Description: Effekt der Zusatzberegnung auf den Ertrag von Hafer KATASTER-BESCHREIBUNG: Erste Versuche zur Bestimmung des Beregnungszeitpunktes von Getreide KATASTER-DETAIL: Delta Nied+ (Mai 〉 73mm), dann kein Effekt einer zusätzlichen Beregnung auf Ertrag bei Hafer und Gerste (Jahr 1931 und 1932)
    Keywords: Berlin, Brandenburg ; 1934 ; Ertrag ; Hafer ; Niederschlag ; Trockenheit ; Gerste
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  • 25
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    In:  Zeitschrift für Hygiene und Infektionskrankheiten 120, 36
    Publication Date: 1937
    Description: 10 000 Erkrankungen und vielen Todesfällen, verursacht durch P. vivax und P. falciparum KATASTER-BESCHREIBUNG: der Sommer war so heiß gewesen, dass eine Übertragung der Erreger der Malaria tropica möglich war KATASTER-DETAIL:
    Keywords: Norddeutschland ; 1826 ; Umweltmedizin ; Infektionskrankheiten
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  • 26
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    In:  Diss. Halle (Saale), Kühn-Archiv, Band 42, 1936
    Publication Date: 1936
    Description: Rangordnungsmethode nach Holdefleiß zur qualitativen Ertragsanalyse, Untersucht wurden die Erträge von Roggen, Weizen, Gerste, Hafer, Erbsen, Pferdebohnen, Hackfrüchte, Rübensamen, Zuckerrüben, Futterrüben, Kartoffeln KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag KATASTER-DETAIL: Delta Sonn (Winter) +, dann Ertrag (Roggen und Weizen) +; Delta T (Winter, September bis März) + und Delta T (Mai, Juni) -, dann Ertrag (Gerste) +; Delta Sonn (Winter) +, dann Ertrag (Sommergetreide) +; Delta T (April, Mai) - und Delta Nied (April, Mai) +, dann Ertrag (Weizen) +; Delta T (Mai bis Juli) - und Delta Nied (Mai bis Juli) +, dann Ertrag (Gerste) +; Delta Nied (April bis Juni) -, dann Ertrag (Hafer) -; Delta Sonn (März) +, dann Ertrag (Hafer) +; Delta Sonn (März) + und Delta T (Mai bis Erntezeit) -, dann Ertrag (Viktoria-Erbse) +; Delta Sonn (Winter) + und Delta Nied (Sommer) +, dann Ertrag (Pferdebohnen) +; Delta Nied +, dann Ertrag (Hackfrüchte) +; Delta Sonn (März, April) +, dann Ertrag (Zuckerrüben) +; Delta Sonn (Winter) +, dann Ertrag (Futterrüben) +; Delta T (September, Oktober - Vorjahr) + und Delta Nied (September, Oktober - Vorjahr) -, dann Ertrag (Kartoffeln) +; Delta Sonn (Winter) +, dann Ertrag (Kartoffeln) +; Delta Nied (April bis Agust) +, dann Ertrag (Kartoffeln) +;
    Keywords: Eichsfeld und Thüringer Becken ; 1900-1931 ; Ertrag ; Getreide ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Trockenheit ; Wassermangel ; Witterung
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  • 27
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    In:  Mitteilungen für die Landwirtschaft 51(Heft 46).
    Publication Date: 1936
    Description: Beobachtungen zum Ernteausfall und dessen Beeinflussung durch den Witterungsverlauf im Jahr 1936. Vergleich mit vergangenen Jahren. KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperatur und Niederschlag in den Monaten April, Mai und Juni und den Reichsertragsschätzungen, bzw. den tatsächlichen Erträgen. Bedeutung eines längeren warmen und niederschlagsarmen Junis für Getreide. KATASTER-DETAIL: Delta T (Juni) -, dann Erträge + Delta T (Juni) + und Niederschlage -, dann Ersträge -
    Keywords: Deutschland ; 1930-1936 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit
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  • 28
    Publication Date: 1937
    Description: Untersuchungen zur Bedeutung der Winterfeuchtigkeit für Roggen bis etwa zum Zeitpunkt des Ährenschiebens, Wechselwirkung Sonnenscheindauer, Temperatur und Niederschlag in unterschiedlichen phänologischen Stadien bei unterschiedlichen Roggensorten und variierender Stickstoffgabe KATASTER-BESCHREIBUNG: Einfluss der Witterung (Sonnenschein, Temperatur, Niederschlag)auf das Wachstum KATASTER-DETAIL: Delta Sonn -, dann Längenwachstum +; Winterfeuchtigkeit +, dann Wachstum +; Delta Nied (von N-Düngung bis Ährenschieben) - und Delta T (von N-Düngung bis Ährenschieben) +, dann Längenwachstum = max; Delta Nied (Hauptvegetationszeit) +, Delta T (Hauptvegetationszeit) -, Delta Sonn (Hauptvegetationszeit) -, dann Längenwachstum +; Delta Nied (Hauptvegetationszeit) + und Delta Wind (Hauptvegetationszeit) +, dann Lagerbildung +;
    Keywords: Brandenburg, Versuchsfeld Bornim bei Potsdam ; 1932-36 ; Ertrag ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Wachstum ; Düngung
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  • 29
    Publication Date: 1937
    Description: Beziehung zwischen Witterungsverlauf und Ertragsleistung KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1900-1935
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  • 30
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    In:  Monthly Notices Roy. astr. Soc., Geophys. Suppl., Kunming, China, D. Reidel Publishing Company, vol. 3, no. 7, pp. 380-388, pp. L09303, (ISSN: 1340-4202)
    Publication Date: 1936
    Keywords: Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Elasticity ; Dislocation
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  • 31
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    National Academy of Science
    In:  Professional Paper, International aspects of oceanography, Washington D.C., National Academy of Science, vol. 3, no. VIIa, pp. 41-50, (ISBN: 3-540-23712-7)
    Publication Date: 1937
    Keywords: Seismology ; Seismicity
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  • 32
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    U. S. Coast and Geodetic Survey
    In:  Bull., Polar Proj. OP-O3A4, Earthquake investigations in California, 1934-35, 231 pp., London, U. S. Coast and Geodetic Survey, vol. 201, no. XVI:, pp. 163-225, (ISBN: 3-540-23712-7)
    Publication Date: 1936
    Keywords: Spectrum ; Seismology ; Seismicity
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  • 33
    Publication Date: 2006-10-26
    Keywords: unknown
    Format: text
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  • 34
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    In:  CASI
    Publication Date: 2019-06-28
    Type: NACA-TN-253
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  • 35
    Publication Date: 2019-06-28
    Type: NACA-TN-565
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  • 36
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    In:  CASI
    Publication Date: 2019-06-28
    Description: This report was made to study the velocity distribution in an open, in a partially open, and in a partially expanding jet. The open-jet observations reveal minor systematic discrepancies from Tollmien's theoretical velocity distribution. The shearing-stress distribution for the partially open jet was determined. The value derived for the ratio of mixing distance to jet width was found to be in close agreement with the corresponding value for the open-jet boundary. The streamline pattern in a partially expanding channel was obtained from the observed velocity distribution and plotted, after which the distribution of the mixing distance for this case was also ascertained.
    Type: NACA-TM-789
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  • 37
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    In:  CASI
    Publication Date: 2019-06-28
    Description: The present report examines the problem of ice formation from the point of view of the pilot and the meteorologist. Their experiences prove the ice deposit to be first and foremost a navigational problem and only secondarily a question of de-icing devices. With correct utilization of the meteorological information by the flyer, ice hazard can in many cases be minimized or avoided. Ice formation and the different types of ice deposits are listed and discussed. Weather formation during these ice deposits are also discussed as well as the effect of ice formation on aircraft.
    Type: NACA-TM-786
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  • 38
    Publication Date: 2019-06-28
    Description: To investigate the process of ignition and combustion in the case of spray injection into heated air, a new form of apparatus is developed and the tests carried out with it described. Photographs of the spray before and after ignition are obtained at frequencies of 500 pictures per second. Pressures and temperatures are simultaneously recorded on oscillograms. Information on the initial conditions, ignition time lag, period of complete combustion, place where ignition starts, and general course of the combustion is obtained.
    Type: NACA-TM-790
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  • 39
    Publication Date: 2019-06-28
    Description: This study will be concerned with the critical examination of two main questions, mainly, susceptibility of centering and more generally, the conditions of static stability, longitudinal equilibrium, and the question of dynamic stability, or at least the damping of longitudinal vibrations about a position of equilibrium that may result from a small variation in the angle of attack.
    Type: NACA-TM-794
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  • 40
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    In:  CASI
    Publication Date: 2019-06-28
    Description: Investigations on the flow phenomena at plates and cambered models were carried out with the aid of force measurements, some pressure distribution measurements, and photographic observation. The experimental methods are described and the results given. Section III of this work gives a comprehensive account of the results and enables us to see how nearly the lift line and lift surface theories agree with the experimental results.
    Type: NACA-TM-798
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  • 41
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    In:  CASI
    Publication Date: 2019-06-28
    Description: Wind tunnel construction and design is discussed especially in relation to subsonic and supersonic speeds. Reynolds Numbers and the theory of compressible flows are also taken into consideration in designing new tunnels.
    Type: NACA-TM-808 , Volta Congress (5th : 1935 : Rome, Italy)
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  • 42
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    In:  CASI
    Publication Date: 2019-06-28
    Description: The apparatus consists of a universal balance with transmission at variable speeds from 300 to 5,000 rpm and a group directly coupled to the model for speeds of 5 to 30,000 revolutions. This new apparatus was also designed with a torsion meter for measuring the torque. Tests were conducted on the effect of the angle between the propeller axis and the wind direction. The results presented correspond to a first series of tests made without an interposed wing and in which the distance between the plane of the propeller disk and the tail was maintained constant.
    Type: NACA-TM-819
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  • 43
    Publication Date: 2019-06-28
    Description: Based on the universal laws of turbulent velocity distribution at rough and smooth walls, there is in the present work presented a method that allows surface roughness tests and in particular, measurements on the roughness of ship surfaces to be carried out in a much simpler manner. The types of roughness investigated were in the form of flat, rough plates installed in a square-section rectangular channel, the other three walls always being smooth. Twenty-one plates of various roughness were investigated, the roughness elements being the following: spheres of diameter 0.41 and 0.21, respectively, spherical segments, cones, and "short" and "long" angles.
    Type: NACA-TM-823
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  • 44
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    In:  CASI
    Publication Date: 2019-06-28
    Description: The present report deals with a number of the main problems requiring solution in the development of helicopters and concerning the lift, flying performance, stability, and drive. A complete solution is given for the stability of the helicopter with rigid blades and control surfaces. With a view to making a direct-lift propeller sufficient without the addition of auxiliary propellers, the "flapping drive" is assessed and its efficiency calculated.
    Type: NACA-TM-827
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  • 45
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    In:  CASI
    Publication Date: 2019-06-28
    Description: The present report offers an approximate theory for the stress and deformation condition after buckling of the skin in reinforced panels and shells loaded in simple shear and compression and under combined stresses. The theory presents a unified scheme for stresses of these types. It is based upon the concept of a nonuniform stress distribution in the metal panel and its marked power of resistance against compressive stresses ("incomplete" tension bay).
    Type: NACA-TM-831
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  • 46
    Publication Date: 2019-06-28
    Description: The report studies the problem of the transport of vorticity or of momentum in light of the Taylor and Prandtl theories which are briefly reviewed. It also show how the formulas of Prandtl could be brought into agreement with experimental results in those cases where they agree with the principle of statistic similitude of Karman, and particularly in the problem of the distribution of velocity and temperature in the wake of a heated cylindrical obstacle.
    Type: NACA-TM-799
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  • 47
    Publication Date: 2019-06-28
    Description: The present report contains a set of charts developed for computing the fixity effect on a compression member in a truss through its adjacent members, the amount of fixity being considered variable with the particular total truss load. The use of the charts is illustrated on two- and three-bay systems, as well as on a triangular truss.
    Type: NACA-TM-800
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  • 48
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    In:  CASI
    Publication Date: 2019-06-28
    Description: The monocoque form of airplane construction has introduced a number of new problems to the stress calculator and the designer. The problems for the stress calculator fall into two groups: the determination of the stress condition (shell statics) and the determination of the failing strength (shell strength). The present report summarizes the most important theoretical and experimental results on this subject.
    Type: NACA-TM-838
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  • 49
    Publication Date: 2019-06-28
    Description: This paper is a critical analysis of the methods of determination of the tendency to detonation. No attempt has been made to describe in detail the different fuels and the different methods proposed.
    Type: NACA-TM-843
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  • 50
    Publication Date: 2019-06-28
    Description: The slot-lip ailerons developed by the NACA consist of a flap-type spoiler with an adjoining continuously open slot. The ailerons were developed in an investigation of the delayed response, or lag, of spoiler-type lateral controls. This report presents the results of tests of these slot-lip ailerons made on wing models in the 7 by 10-foot wind tunnel, on a Fairchild 22 airplane in the full-scale wind tunnel and in flight, and on the Weick W1-A airplane in flight.
    Type: NACA-TR-602
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  • 51
    Publication Date: 2019-06-28
    Description: Report presents the results of tests of a 1/10-scale model of the XN2Y-1 airplane tested in the NACA 5-foot vertical wind tunnel in which the six components of forces and moments were measured. The model was tested in 17 attitudes in which the full-scale airplane had been observed to spin, in order to determine the effects of scale, tunnel, and interference. In addition, a series of tests was made to cover the range of angles of attack, angles of sideslip, rates of rotation, and control setting likely to be encountered by a spinning airplane. The data were used to estimate the probable attitudes in steady spins of an airplane in flight and of a model in the free-spinning tunnel. The estimated attitudes of steady spin were compared with attitudes measured in flight and in the spinning tunnel. The results indicate that corrections for certain scale and tunnel effects are necessary to estimate full-scale spinning attitudes from model results.
    Type: NACA-TR-607
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  • 52
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation of the general aerodynamic characteristics of the NACA 23012 and 23021 airfoils, each equipped with a 0.20c external flap of NACA 23012 section. The tests were made in the NACA 7 by 10-foot and variable-density wind tunnels and covered a range of Reynolds numbers that included values corresponding to those for landing conditions of a wide range of airplanes. Besides a determination of the variation of lift and drag characteristics with position of the flap relative to the main airfoil, complete aerodynamic characteristics of the airfoil-flap combination with a flap hinge axis selected to give small hinge moments were measured in the two tunnels. Some measurements of air loads on the flap itself in the presence of the wing were made in the 7 by 10-foot wind tunnel.
    Type: NACA-TR-573
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  • 53
    Publication Date: 2019-06-28
    Description: Report presents the results of an experimental investigation made in the NACA full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing. The results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the 20-foot wind tunnel and reported in technical reports 415, 462, 505, 506, and 507.
    Type: NACA-TR-569
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  • 54
    Publication Date: 2019-06-28
    Description: This report presents the results of an analytical study of the lateral controllability of an airplane in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. The investigation was undertaken partly for the purpose of coordinating the results of a long series of wind-tunnel investigations with phenomena observed in flight tests; for this reason a hypothetical average airplane, embodying the essential characteristics of both wind-tunnel models and the full-size test airplanes, was assumed for the study.
    Type: NACA-TR-570
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  • 55
    Publication Date: 2019-06-28
    Description: Two methods were used to measure fuel distribution within sprays from several types of fuel-injection nozzles. A small tube inserted through the wall of an air tight chamber into which the sprays were injected could be moved about inside the chamber. When the pressure was raised to obtain air densities of 6 and 14 atmospheres, some air was forced through the tube and the fuel that was carried with it was separated by absorbent cotton and weighed. Cross sections of sprays from plain, pintle, multiple-orifice, impinging-jets, centrifugal, lip, slit, and annular-orifice nozzles were investigated, at distances of 1, 3, 5, and 7 inches from the nozzles.
    Type: NACA-TR-565
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  • 56
    Publication Date: 2019-06-28
    Description: This report presents the results of full-scale wind tunnel tests conducted to determine the ground-handling forces on a 1/40-scale model of the U. S. Airship "Akron." Ground-handling conditions were simulated by establishing a velocity gradient above a special ground board in the tunnel comparable with that encountered over a landing field. The tests were conducted at Reynolds numbers ranging from 5,000,000 to 19,000,000 at each of six angles of yaw between 0 degree and 180 degrees and at four heights of the model above the ground board. The ground-handling forces vary greatly with the angle of yaw and reach large values at appreciable angles of yaw. Small changes in height, pitch, or roll did not critically affect the forces on the model. In the range of Reynolds numbers tested, no significant variation of the forces with the scale was disclosed.
    Type: NACA-TR-566
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  • 57
    Publication Date: 2019-06-28
    Description: Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are presented.
    Type: NACA-TR-563
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  • 58
    Publication Date: 2019-06-28
    Description: A simplified treatment of the application of Heaviside's operational methods to problems of airplane dynamics is given. Certain graphical methods and logarithmic formulas that lessen the amount of computation involved are explained. The problem representing a gust disturbance or control manipulation is taken up and it is pointed out that in certain cases arbitrary control manipulations may be dealt with as though they imposed specific constraints on the airplane, thus avoiding the necessity of any integration. The application of the calculations described in the text is illustrated by several examples chosen to show the use of the methods and the practicability of the graphical and logarithmic computations described.
    Type: NACA-TR-560
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  • 59
    Publication Date: 2019-06-28
    Description: Report presents the results of a series of 10-foot-diameter autogiro rotor models tested in the NACA 20-foot wind tunnel. Four of the models differed only in the airfoil sections of the blades, the sections used being the NACA 0012, 0018, 4412, and 4418. Three additional models employing the NACA 0012 section were tested, in which a varying portion of the blade near the hub was replaced by a streamline tube with a chord of about one-fourth the blade chord.
    Type: NACA-TR-552
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  • 60
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: A description of the test methods used at the National Bureau of Standards for determining the characteristics of aircraft compasses is given. The methods described are particularly applicable to compasses in which mineral oil is used as the damping liquid. Data on the viscosity and density of certain mineral oils used in United States Navy aircraft compasses are presented. Characteristics of Navy aircraft compasses IV to IX and some other compasses are shown for the range of temperatures experienced in flight. Results of flight tests are presented. These results indicate that the characteristic most desired in a steering compass is a short period and, in a check compass, a low overswing.
    Type: NACA-TR-551
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  • 61
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation conducted to study the effects of the inert gases, argon and helium, upon flame speed and expansion ratio in exploding mixtures of carbon monoxide, oxygen and water.For the particular gas mixtures investigated the results show that: (1) With the possible exception of helium in small amounts the addition of inert gas always produces decreased flame speed and expansion ratio; (2) like volumes of argon and helium have very different effects upon flame speed but practically the same effect upon expansion ratio; and (3) the difference in the effect of these two gases upon speed is independent of the ratio of carbon monoxide to oxygen. A discussion of some possible modes by which inert gases may produce the observed effects is included.
    Type: NACA-TR-553
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  • 62
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests to determine the effect of wing-tip shape and dihedral on some of the aerodynamic characteristics of Clark Y wings that affect the performance and lateral stability of airplanes. Force tests at several angles of yaw and rotation tests at zero yaw were made. From these tests the rates of change of rolling moment, yawing moment, and cross-wind force coefficients with angle of yaw and the rate of change of rolling moment coefficient with rolling were determined.
    Type: NACA-TR-548
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  • 63
    Publication Date: 2019-06-28
    Description: This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA variable-density wind tunnel to provide information regarding the effects of aerodynamic interference between wings and fuselages at a large value of Reynolds number.
    Type: NACA-TR-540
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  • 64
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests of a wing in combination with each of three sizes of Fowler flap. The purpose of the investigation was to determine the aerodynamic characteristics as affected by flap chord and position, the air loads on the flaps, and the effect of flaps on the downwash.
    Type: NACA-TR-534
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  • 65
    Publication Date: 2019-06-28
    Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Type: NACA-AR-21
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  • 66
    Publication Date: 2019-06-28
    Description: The interference of the wind-tunnel boundaries on the downwash behind an airfoil has been experimentally investigated and the results have been compared with the available theoretical results for open-throat wind tunnels. As in previous studies, the simplified theoretical treatment that assumes the test section to be an infinite free jet has been shown to be satisfactory at the lifting line. The experimental results, however, show that this assumption may lead to erroneous conclusions regarding the corrections to be applied to the downwash in the region behind the airfoil where the tail surfaces are normally located. The results of a theory based on the more accurate concept of the open-jet wind tunnel as a finite length of free jet provided with a closed exit passage are in good qualitative agreement with the experimental results.
    Type: NACA-TR-609
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  • 67
    Publication Date: 2019-06-28
    Description: This report discusses the fundamental action of shear deformation of the flanges on the basis of simplifying assumptions. The theory is developed to the point of giving analytical solutions for simple cases of beams and of skin-stringer panels under axial load. Strain-gage tests on a tension panel and on a beam corresponding to these simple cases are described and the results are compared with analytical results. For wing beams, an approximate method of applying the theory is given. As an alternative, the construction of a mechanical analyzer is advocated.
    Type: NACA-TR-608
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  • 68
    Publication Date: 2019-06-28
    Description: This report presents the results of test made to determine the rolling friction of airplane wheels and tires under various conditions of wheel loading, tire inflation pressure, and ground surface. The effect of wheel-bearing type was also investigated. Six pairs of wheels and tires were tested including two sizes of each of the types designated as standard (high pressure), low pressure, and extra low pressure. The results of calculations intended to show the effect of variations in rolling friction on take-off are also presented.
    Type: NACA-TR-583
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  • 69
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: This report is a revision of NACA-TR-357. It was prepared by the Committee on Aircraft Accidents. The purpose of this report is to provide a basis for the classification and comparison of aircraft accidents, both civil and military.
    Type: NACA-TR-576
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  • 70
    Publication Date: 2019-06-28
    Description: The cooling of a single-row radial air-cooled engine using several cowling arrangements has been studied in the NACA 20-foot wind tunnel. The results show the effect of the propeller and several cowling arrangements on cooling for various values of the indicated horsepower in the climb condition. A table giving comparative performance of the various cowling arrangements is presented. The dependence of temperature on indicated horsepower and pressure drop across the baffles is shown by charts. Other charts show the limiting indicated horsepower against the pressure drop across the engine and the heat dissipated at various values of the indicated horsepower.
    Type: NACA-TR-596
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  • 71
    Publication Date: 2019-06-28
    Description: An extended experimental study has been made in regard to the various refinements in the design of engine cowlings as related to the propeller-nacelle unit as a whole, under conditions corresponding to take-off, climb, and normal flight. The tests were all conducted at full scale in the 20-foot wind tunnel. This report presents the results of a novel type of engine cowling, characterized by the fact that the exit opening discharging the cooling air is not, as usual, located behind the engine but at the foremost extremity or nose of the cowling. The efficiency is found to be high, owing to the fact that higher velocities may be used in the exit opening.
    Type: NACA-TR-595
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  • 72
    Publication Date: 2019-06-28
    Description: Report presents the results of a comprehensive experimental study carried out at full scale in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the functioning of the power plant and propeller unit under different conditions. This report deals particularly with the problem of the cooling of an airplane engines on the ground. The influence of different nose forms, skirts, flaps, propellers, spinners, and special blowers has been investigated.
    Type: NACA-TR-593
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  • 73
    Publication Date: 2019-06-28
    Description: This investigation is part of an extensive experimental study that has been carried out at full scale in the NACA 20-foot tunnel, the purpose of which has been to furnish information in regard to the functioning of the propeller-cowling-nacelle unit under all conditions of take-off, climbing, and normal flight. This report presents the results of tests of six propellers in the normal and high-speed flight range and also includes a study of the take-off characteristics.
    Type: NACA-TR-594
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  • 74
    Publication Date: 2019-06-28
    Description: This report describes an investigation using a stroboscopic apparatus for observing flame movement through a large number of small windows distributed over the head of a spark-ignition engine in following flame spread with combustion chambers of different shapes at two engine speed and for a variety of spark-plug locations including single and twin ignition. The principal factors influencing flame movement in the engine are discussed, and the lack of reliable information regarding their separate effects upon the structure of the flame and its speed of propagation are emphasized.
    Type: NACA-TR-556
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  • 75
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation of a systematically chosen representative group of related airfoils conducted in the NACA variable-density wind tunnel over a wide range of Reynolds number extending well into the flight range. The tests were made to provide information from which the variations of airfoil section characteristics with changes in the Reynolds number could be inferred and methods of allowing for these variations in practice could be determined. This work is one phase of an extensive and general airfoil investigation being conducted in the variable-density tunnel and extends the previously published researches concerning airfoil characteristics as affected by variations in airfoil profile determined at a single value of the Reynolds number.
    Type: NACA-TR-586
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  • 76
    Publication Date: 2019-06-28
    Description: The investigation of wind-tunnel turbulence, conducted at the National Bureau of Standards with the cooperation of the National Advisory Committee for Aeronautics, has been extended to include a new variable, namely, the scale of the turbulence. This report presents the results of a study of this new variable together with the intensity of the turbulence, and the effect of both on the critical Reynolds number of spheres.
    Type: NACA-TR-581
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  • 77
    Publication Date: 2019-06-28
    Description: Fuel was injected from different type of injection nozzles into the combustion chamber of the NACA combustion apparatus, operated as a compression-ignition engine. High speed motion pictures were taken of the fuel sprays and combustion. Single-orifice nozzles of 0.008, 0.020, and 0.040 inch diameter, and multiorifice nozzles having 2, 6, and 16 orifices were tested. Nozzles having impinging jets and slit orifices were also included. The photographs indicate that the rate of vapor diffusion from the spray is comparatively slow and that this slow rate of diffusion for combustion chambers with little or no air flow prevents the compression-ignition engine from giving the high performance inherent in the high compression ratios. The sprays from the multiorifice nozzles destroyed the air movement to a greater extent than did those from single orifice nozzles. It is concluded that high performance cannot be realized until the methods of distributing the fuel are improved by means of the injection-nozzle design, air flow, or both.
    Type: NACA-TR-561
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  • 78
    Publication Date: 2019-06-28
    Description: This report deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined. The "Friedrichs-Von Karman equations" are shown to require the least amount of labor. Numerical examples by the several methods of analysis are given and the agreement between the calculation and experiment is shown.
    Type: NACA-TR-508
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  • 79
    Publication Date: 2019-06-28
    Description: This report gives the results of an investigation conducted in the NACA full-scale wind tunnel on a small parasol monoplane equipped with three different split trailing-edge wing flaps. The object of the investigation was to determine and correlate data on the characteristics of the airplane and flaps as affected by variation in flap chord, flap deflection, and flap location along the wing chord. The results give the lift, the drag, and the pitching moment characteristics of the airplane, and the flap forces and moments, the pressure distribution over the flaps and wing at one section, and the downwash characteristics of the flap and wing combinations.
    Type: NACA-TR-539
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  • 80
    Publication Date: 2019-06-28
    Type: NACA-TN-630
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  • 81
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: The N.A.C.A. has developed a simple pressure-level meter for the measurement of sound-pressure levels above 70 db. The instrument employs a carbon microphone but has no amplification. The source of power is five flashlight batteries. Measurements may be made up to the threshold of feeling with an accuracy of plus or minus 2 db; band analysis of complex spectra may be made if desired.
    Type: NACA-TN-629
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  • 82
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: The purpose here is to consider the mechanical characteristics of reinforced phenol-formaldehyde resin as related to its use as structural material for aircraft. Data and graphs that have appeared in the literature are reproduced to illustrate the comparative behavior of plastics and materials commonly used in aircraft construction. Materials are characterized as to density, static strength, modulus of elasticity, resistance to long-time loading, strength under repeated impact, energy absorption, corrosion resistance, and ease of fabrication.
    Type: NACA-TN-628
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  • 83
    Publication Date: 2019-06-28
    Description: An investigation was made in the N.A.C.A. 7 by 10 foot wind tunnel of the distribution of air pressure over one chord section of a Clark Y-H airfoil with a split flap. The results obtained are given in the form of diagrams showing the chordwise distribution of pressure on both airfoil and flap as plots of calculated aerodynamic coefficients for both airfoil and flap.
    Type: NACA-TN-627
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  • 84
    Publication Date: 2019-06-28
    Description: This report presents the results of a combined theoretical and experimental investigation conducted at the Georgia School of Technology on the static thrust of the lifting air screw of the type used in modern autogiros and helicopters. The theoretical part of this study is based on Glauert's analysis but certain modifications are made that further clarify and simplify the problem. Of these changes the elimination of the solidity as an independent parameter is the most important. The experimental data were obtained from tests on four rotor models of two, four, and five blades and, in general, agree quite well with the theoretical calculations. The theory indicates a method of evaluating scale effects on lifting air screws, and these corrections have been applied to the model results to derive general full-scale static thrust, torque, and figure-of-merit curves for constant-chord, constant-incidence rotors. Convenient charts are included that enable hovering flight performance to be calculated rapidly.
    Type: NACA-TN-626
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  • 85
    Publication Date: 2019-06-28
    Type: NACA-TN-625
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  • 86
    Publication Date: 2019-06-28
    Description: Bending tests were made of two circular cylinders of corrugated aluminum-alloy sheet. In each test failure occurred by bending of the corrugations in a plane normal to the skin. It was found, after analysis of the effect of short end bays, that the computed stress on the extreme fiber of a corrugated cylinder is in excess of that for a flat panel of the same basic pattern and panel length tested as a pin-ended column. It is concluded that this increased strength was due to the effects of curvature of the pitch line. It is also concluded from the tests that light bulkheads closely spaced strengthen corrugated cylinders very materially.
    Type: NACA-TN-595
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  • 87
    Publication Date: 2019-06-28
    Description: Measurements were made of the maximum push, pull, and tangential forces that could be applied to airplane wheel-type controls for a wide range of fore-and-aft positions of the wheel. The measurements were conducted with several sizes of wheels and several heights of the center of the wheel above the seat. Various one and two-hand grips with pilots both secure and free were studied for each of the two pilots used in the investigation.
    Type: NACA-TN-623
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  • 88
    Publication Date: 2019-06-28
    Description: Wind tunnel and flight tests were made to determine the performance characteristics of two designs of commercially available venturi tubes used in airplanes to operate air-driven gyroscopic instruments. Data obtained at sea level may be used to make approximate predictions of performance at higher altitudes. There is some indication that this may also be done for single venturi tubes. For a given installation in which an air-driven instrument is connected through tubing with a venturi tube, the volume rate of induced air flow is approximately proportional to the product of indicated air speed and the square root of the ratio of standard to ambient air pressure. The efficiency of such a system at a given altitude is constant. Rather large variations in suction and efficiency were found for individual tubes of the same design. Cylindrical fairings on the external surface resulted in a reduction of both drag and suction but little change in efficiency.
    Type: NACA-TN-624
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  • 89
    Publication Date: 2019-06-28
    Description: The results of tests made in the N.A.C.A. tank on two models of flying-boat hulls to determine the effect of ventilating the step are given graphically. The step of N.A.C.A. model 11-C was ventilated in several different ways and it was found that the resistance of the normal form is not appreciably affected by artificial ventilation in any of the forms tried. Further tests made with the depth of the step of model 11-C reduced likewise show no appreciable effect on the resistance from ventilation of the step. Tests were made on a model of the hull of the Navy P3M-1 flying-boat hull both with and without ventilation of the step. It was found that the discontinuity which is obtained in the resistance curves of this model is eliminated by ventilating the step.
    Type: NACA-TN-594
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  • 90
    Publication Date: 2019-06-28
    Description: Data are presented to show the extent to which the maximum lift coefficient and consequently the minimum speed of an airplane, determined by flight tests, may vary with test conditions. The data show that cl-max may vary as much as 14 percent, depending on the altitude and wing loading at which the tests were made, the position or motion of the propeller, and the rate at which the angle of attack is changing when the maximum lift coefficient is obtained. The variation of the maximum lift coefficient with these factors, which are under the control of the test engineer, shows the need of standardizing the test procedure. A further variation is shown with wing conditions as affected by weathering and vibration, factors that cannot be completely controlled.
    Type: NACA-TN-622
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  • 91
    Publication Date: 2019-06-28
    Description: The pressure drop across finned cylinders in a jacket for a range of air speeds from approximately 13 to 230 miles per hour has been investigated. Tests were made to determine the effect on the pressure drop of changes in fin space, fin width, jacket entrance and exit areas, skirt-approach radius, and the use of fillets and a separator plate at the rear of the cylinder. The pressure drop across the cylinder increased as the fin space decreased, the increase being very rapid at fin spaces smaller than approximately 0.20 inch. Fin width had little effect on the pressure drop for the range of widths tested. The pressure drop across the cylinder was nearly halved by increasing the skirt-approach radius from 3/4 inch to 1-1/4 inches, but fillets and a separator plate at the rear of the cylinder had little effect on the pressure drop. The pressure drop across a cylinder with tapered fins was greater than that for a cylinder having rectangular fins with the same effective fin spacing.
    Type: NACA-TN-621
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  • 92
    Publication Date: 2019-06-28
    Description: A study was made of the most important factors affecting the range of airplanes. Numerical examples are given showing the effects of different variables on the range of a two-engine airplane. The takeoff problems of long-range airplanes are analyzed.
    Type: NACA-TN-592
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  • 93
    Publication Date: 2019-06-28
    Description: The theoretical basis of calculation of pressure drop in tubing is reviewed briefly. The effect of pressure drop in connecting tubing upon the operation and indication of aircraft instruments is discussed. Approximate equations are developed, and charts and tables based upon them are presented for use in designing installations of altimeters, air-speed indicators, rate-of-climb indicators, and air-driven gyroscopic instruments.
    Type: NACA-TN-593
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  • 94
    Publication Date: 2019-06-28
    Description: A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that cooling can be improved by 20 percent by using a correctly designed baffle. Such a gain is as effective as a 65 percent increase in pressure drop across the standard baffle, which had a 1/4 inch clearance between baffle and fin tips.
    Type: NACA-TN-620
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  • 95
    Publication Date: 2019-06-28
    Description: Engine test results are presented for simulated altitude conditions. A displaced-piston combustion chamber on a 5- by 7-inch single cylinder compression-ignition engine operating at 2,000 r.p.m. was used. Inlet air temperature equivalent to standard altitudes up to 14,000 feet were obtained. Comparison between performance at altitude of the unsupercharged compression-ignition engine compared favorably with the carburetor engine. Analysis of the results for which the inlet air temperature, inlet air pressure, and inlet and exhaust pressure were varied indicates that engine performance cannot be reliably corrected on the basis of inlet air density or weight of air charge. Engine power increases with inlet air pressure and decreases with inlet air temperatures very nearly as straight line relations over a wide range of air-fuel ratios. Correction factors are given.
    Type: NACA-TN-619
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  • 96
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: Discussed here are results already achieved with sonic altimeters in light of the theoretical possibilities of such instruments. From the information gained in this investigation, a procedure is outlined to determine whether or not a further development program is justified by the value of the sonic altimeter as an aircraft instrument. The information available in the literature is reviewed and condensed into a summary of sonic altimeter developments. Various methods of receiving the echo and timing the interval between the signal and the echo are considered. A theoretical discussion is given of sonic altimeter errors due to uncertainties in timing, variations in sound velocity, aircraft speed, location of the sending and receiving units, and inclinations of the flight path with respect to the ground surface. Plots are included which summarize the results in each case. An analysis is given of the effect of an inclined flight path on the frequency of the echo. A brief study of the acoustical phases of the sonic altimeter problem is carried through. The results of this analysis are used to predict approximately the maximum operating altitudes of a reasonably designed sonic altimeter under very good and very bad conditions. A final comparison is made between the estimated and experimental maximum operating altitudes which shows good agreement where quantitative information is available.
    Type: NACA-TN-611
    Format: application/pdf
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  • 97
    Publication Date: 2019-06-28
    Description: Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 airfoil equipped with 20 percent chord split trailing-edge flaps of various spans. A special installation was employed in the tests utilizing a half-span airfoil mounted vertically above a reflection plane. The airfoil has a constant chord center section and rounded tips and is tapered in thickness from 18 percent c at the root to 9 percent c at the tip. The aerodynamic characteristics, given by the usual dimension less coefficients, are presented graphically as functions of flap span and angle of attack as well as by semispan load diagrams. The results indicate, in general, that only a relatively small increase in the normal-force coefficient is to be expected by extending the flap span of an airfoil-flap combination, similar to the one tested, beyond 70 percent of the wing span.
    Type: NACA-TN-591
    Format: application/pdf
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  • 98
    Publication Date: 2019-06-28
    Description: This paper is essentially a consideration of mass balance of ailerons from a preliminary design standpoint, in which the extra weight of the mass counterbalance is the most important phase of the problem. Equations are developed for the required balance weight for a simple aileron and this weight is correlated with the mass-balance coefficient. It is concluded the location of the c.g. of the basic aileron is of paramount importance and that complete mass balance imposes no great weight penalty if the aileron is designed to have its c.g. inherently near to the hinge axis.
    Type: NACA-TN-609
    Format: application/pdf
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  • 99
    Publication Date: 2019-06-28
    Description: Curves of forced frequency against amplitude are presented for the conditions where the forced frequency is both increased and decreased into the resonant range. On the basis of these curves it is shown that the practical resonance frequency is the point where wrinkling first occurs and that the resonance frequency will be subject to considerable travel once permanent wrinkles appear in the vibrating shell. The decreasing mode of striking resonance is found to be by far the most destructive condition.
    Type: NACA-TN-607
    Format: application/pdf
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  • 100
    Publication Date: 2019-06-28
    Description: An investigation was made to determine the effect of variations in the horizontal and vertical air-entry angles on the performance characteristics of a single-cylinder 2-stroke-cycle compression-ignition test engine. Performance data were obtained over a wide range of engine speed, scavenging pressure, fuel quantity, and injection advance angle with the optimum guide vanes. Friction and blower-power curves are included for calculating the indicated and net performances. The optimum horizontal air-entry angle was found to be 60 degrees from the radial and the optimum vertical angle to be zero, under which conditions a maximum power output of 77 gross brake horsepower for a specific fuel consumption of 0.52 pound per brake horsepower-hour was obtained at 1,800 r.p.m. and 16-1/2 inches of Hg scavenging pressure. The corresponding specific output was 0.65 gross brake horsepower per cubic inch of piston displacement. Tests revealed that the optimum scavenging pressure increased linearly with engine speed. The brake mean effective pressure increased uniformly with air quantity per cycle for any given vane angle and was independent of engine speed and scavenging pressure.
    Type: NACA-TN-610
    Format: application/pdf
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