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  • Other Sources  (162)
  • 2010-2014
  • 1980-1984
  • 1925-1929  (162)
  • 1927  (162)
  • 1
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    Die Veränderung der Erdkruste durch Fließbewegungen der Kontinentalscholle (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 16, no. 3, pp. 239-247, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; Tectonics ; Inelastic ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Der Aufbau der Erdkruste (1927)
    In:  Zeitschrift für Geophysik, Jena, Gustav Fischer, vol. 3, no. 3, pp. 371-377, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; CRUST
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Die Bodenunruhe durch Brandung (1927)
    In:  Zeitschrift für Geophysik, Jena, Gustav Fischer, vol. 3, no. 3, pp. 328-329, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: NOISE ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Die Veränderung der Erdkruste durch Fließbewegungen II (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 18, no. 3, pp. 281-291, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; Tectonics ; Inelastic ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Ebbe und Flut (1927)
    J. A. Barth
    In:  Professional Paper, Handbuch der physikalischen und technischen Mechanik, Bd. V, Leipzig, J. A. Barth, vol. 3, no. VIIa, pp. 366-391, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1927
    Keywords: NOISE ; TIDES
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    W. Milch† (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 17, no. 3, pp. 443, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Nachruf
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Die Veränderung der Erdkruste durch Fließbewegungen der Kontinentalscholle (1927)
    In:  Geologische Rundschau, Jena, Gustav Fischer, vol. 18, no. 3, pp. 148-149, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earth model, also for more shallow analyses ! ; Tectonics ; Inelastic ; Plate tectonics
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Die Geschwindigkeit der Longitudinalwellen im Erdinnern (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 17, no. 3, pp. 356-365, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Travel time ; Earth model, also for more shallow analyses ! ; Seismology ; Body waves ; Velocity depth profile
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Die Bedeutung der Isostasie (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 16, no. 3, pp. 396-403, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Gravimetry, Gravitation ; Static case
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Die Herdtiefe der Süddeutschen Beben 1911 und 1913 (1927)
    In:  Gerlands Beiträge zur Geophysik, Jena, Gustav Fischer, vol. 18, no. 3, pp. 379-382, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1927
    Keywords: Earthquake ; Hypocentral depth ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Erdbeben und Erdbebenwellen (1927)
    J. A. Barth
    In:  Professional Paper, Handbuch der physikalischen und technischen Mechanik, Bd. III, Leipzig, J. A. Barth, vol. 3, no. VIIa, pp. 387-420, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1927
    Keywords: Seismology ; Seismicity ; Waves
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Welchen Einfluss hat die ungünstige Witterung dieses Winters auf die Entwicklung unserer Kulturpflanzen? (1927)
    In:  Hannov. land- und forstw. Zeitg.:93-95
    Details
    Publication Date: 1927
    Description: Beschreibung der Witterungsverläufe der Winter und Empfehlungen für die Bodenbearbeitung und Bestandesführung von Winterkulturen KATASTER-BESCHREIBUNG: Einfluss der Witterung (Niederschlag und Temperatur) auf den Ertrag KATASTER-DETAIL: Delta Nied (Vorjahr) ++, dann Ertrag -; Delta Nied (Winter) +, dann Bodenfeuchte + und somit Ertrag +; Delta T (November) -, dann Ertrag -; Delta T (Winter) +, dann Ertrag +; Delta T (Frühling) +, dann Ertrag -;
    Keywords: Niedersachsen ; 1924-26 ; Insekten ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Pflanzenschädling ; Roggen ; Weizen ; Düngung ; Gerste
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  • 13
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    Die Weißährigkeit des Weizens und ihre Ursachen (Ophiobolus herpotrichus u.a.) (1927)
    In:  Landwirtschaftliche Wochenschrift der Provinz Sachsen und Anhalt 29; p.668-670
    Details
    Publication Date: 1927
    Description: Der Autor führt aufgrund von Beobachtungen das Auftreten der Weißährigkeit auf Fußkrankheiten und Fusariumpilze, sowie landwirtschaftliche Praktiken zurück. In einem kleinen Abschnitt wird auch auf den Einfluß von Witterung und Bodenverhältnissen eingegangen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Sachsen, Sachsen-Anhalt ; 1926-1927 ; Getreide ; Pflanzenkrankheit ; Weizen
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  • 14
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    Das gegenwärtige und frühere Vorkommen der Malaria und die Verbreitung der Anophelesmücken im Gebiete des Deutschen Reiches (1927)
    In:  Arbeiten aus dem Reichsgesundheitsamte 59
    Details
    Publication Date: 1927
    Keywords: Deutschland ; Umweltmedizin ; Infektionskrankheiten
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  • 15
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    Floren-Elemente und Temperaturverteilung in Deutschland. (1927)
    In:  Ber. Deut. Bot. Gesellschaft 45:638-643.
    Details
    Publication Date: 1927
    Description: Einfluss der Temperatur auf die Flora und ihre Verteilung in Deutschland KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; Botanik ; Klima ; Phänologie ; Temperatur
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  • 16
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    Frostschäden an Obstbäumen in Dahlem. (1927)
    In:  Nachrichtenbl. Deut. Pflanzenschutzdienst 9 (5):38.
    Details
    Publication Date: 1927
    Description: Frostschäden an Obstbäumen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Berlin-Dahlem ; 1924-26 ; Forst ; Obst
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  • 17
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    Die Beziehung zwischen Bodentemperatur und Lufttemperatur und ihrem Einfluss auf den Ernteertrag. (1927)
    In:  Fortschr. Landw. 2:205-212.
    Details
    Publication Date: 1927
    Description: Untersuchungen über die Gründe für die schlechte Getreideernte im Donau-Einzugsgebiet des Jahres 1924, Zusammenhang zwischen der Luft- und Bodentemperatur, dem Pflanzenwachtum und dem Ertrag KATASTER-BESCHREIBUNG: Korn-Stroh-Verhältnis wird beeinflusst von dem Verhältnis der Boden- zur Lufttemperatur, KATASTER-DETAIL: Delta T (Diff. Boden zu Luft im Mai) 〈 0, dann ertragsrelevant
    Keywords: Bayern ; 1913-15, 1924-26 ; Ertrag ; Getreide ; Temperatur ; Frost
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  • 18
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    Über Beziehungen zwischen der Witterung und den Ernteerträgen in Preußen. (1927)
    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 6:490-496.
    Details
    Publication Date: 1927
    Description: Einfluss der Witterungsfaktoren Niederschlag, Temperatur und Sonnenscheindauer auf die Erträge KATASTER-BESCHREIBUNG: Einteilung der Temperatur in Klassen (stark, mittel, gering) und die Beurteilung auf die Erträge in den 6 Provinzen des deutschen Reiches, mit Vermehrung der Niederschlage wahrend der Vegetationszeit Zunahme der Halmfrüchte und der Kartoffeln im gröBten Teile des PreuBischen Staates anfangs, jedoch nd spater wieder abnehmender Trend KATASTER-DETAIL: Delta T+ (April-Augut), dann Winterweizenerträge + in OstpreuBen, Brandenburg und Sachsen Delte T++ (April-August), dann Winterweizenerträge ++ in Ostpreußen, aber - in Brandenburg und Sachsen Delta T- (April-Augut), dann Winterweizenerträge - in Hannover und der Rheinprovinz Delta T+ (+0.1° Erhöhung Temperaturmittel der Monate April bis September), dann Kartoffel+ in OstpreuBen und Schlesien
    Keywords: Deutschland, teilw. einzelne Regionen ; 1899-1913 ; Ertrag ; Niederschlag ; Temperatur ; Witterung ; Sonnenscheindauer
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  • 19
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    Der jährliche Gang der Lufttemperatur und die Vegetationsperiode (1927)
    In:  Met. Zeitschr. 44:13-18.
    Details
    Publication Date: 1927
    Description: Beobachtungsergebnisse von 650 Stationen, Ergänzungen zu den ersten Veröffentlichungen von Köppen, geographische Lage und die Nähe des Wassers ist entscheidend für jährlichen Temperaturverlauf und damit die Vegetation und die Vegetationsperiode KATASTER-BESCHREIBUNG: Zusammenhang zwischen jährlichem Temperaturverlauf (und damit der Vegetation und der Vegetationsperiode) und der geographischen Lage sowie der Nähe des Wassers KATASTER-DETAIL: Nähe zum Wasser +,dann Delta T von Januar zu Februar - und somit Verspätung im Jahresgang +
    Keywords: Europäischer Teil von Russland ; 1881-1915 ; Temperatur ; Vegetationsperiode
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  • 20
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    Die Feldberegnung in Mitteldeutschland (1927)
    In:  Arb. deut. Landw. Gesell. 354:66
    Details
    Publication Date: 1927
    Description: Zusammenhang zwischen dem Ertrag von Kartoffeln, Hafer und Luzerne und dem Niederschlag KATASTER-BESCHREIBUNG: Korrelationen zwischen dem Ertrag von Kartoffeln und Hafer und dem jährlichen Niederschlag, bzw. der jährlichen Anzahl nasser Monate (〉50mm pro Monat); stärkerer Zusammenhang mit jährlichem Niederschlag als mit Anzahl nasser Monate und umso schwächer, je niederschlagsreicher das Jahr, am ausgeprägtesten in Mitteldeutschland selbst auf schweren Böden KATASTER-DETAIL:
    Keywords: Mitteldeutschland ; 1904-1914, 1922-1924 ; Kartoffeln ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag
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  • 21
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    Das "Bioklimatische Gesetz von Hopkins und der Versuch seiner Nutzbarmachung für die Landwirtschaft (1927)
    In:  In: Nachrichtenbl. deutsch. Pflanzenschutzdienst; p. 35-36, 43-44
    Details
    Publication Date: 1927
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  • 22
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    Das gegenwärtige und frühere Vorkommen der Malaria und die Verbreitung der Anophelesmücken im Gebiete des Deutschen Reiches. (1927)
    In:  Arbeiten aus dem Reichsgesundheitsamte, 59, 1-428
    Details
    Publication Date: 1927
    Description: mit Karte, autochthone P. falciparum- Infektionen in Deutschland, 1922 20 Tropica- Fälle in Berlin, 1923 4 Fälle KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, Berlin
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  • 23
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    Grundlagen der Erdbebenkunde (1927)
    Bornträger
    In:  Berlin, Bornträger, vol. 12, 189 S., no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1927
    Keywords: Textbook of geophysics ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 24
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    Measurement of the moments of inertia of full scale airplanes (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-265
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  • 25
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    The Characteristics of the N.A.C.A 97, Clark Y, and N.A.C.A. M6 Airfoils with Particular Reference to the Angle of Attack (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-270
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  • 26
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    Junkers Commercial Airplane G 31 (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The three engine Junkers commercial Airplane, type G 31 is a further development of the earlier G 24. It is an all metal low wing monoplane with a total engine output of 1100-1200 HP.
    Type: NACA-AC-54
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  • 27
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    Pressure Distribution Over Airfoils at High Speeds (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with the pressure distribution over airfoils at high speeds, and describes an extension of an investigation of the aerodynamic characteristics of certain airfoils which was presented in NACA Technical Report no. 207. The results presented in report no. 207 have been confirmed and extended to higher speeds through a more extensive and systematic series of tests. Observations were also made of the air flow near the surface of the airfoils, and the large changes in lift coefficients were shown to be associated with a sudden breaking away of the flow from the upper surface. The tests were made on models of 1-inch chord and comparison with the earlier measurements on models of 3-inch chord shows that the sudden change in the lift coefficient is due to compressibility and not to a change in the Reynolds number. The Reynolds number still has a large effect, however, on the drag coefficient. The pressure distribution observations furnish the propeller designer with data on the load distribution at high speeds, and also give a better picture of the air-flow changes.
    Type: NACA-TR-255
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  • 28
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    A Comparison of the Take-off and Landing Characteristics of a Number of Service Airplane (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation, which is a continuation of Technical Report 154, follows very closely the earlier methods and covers a number of service airplanes, whereas the previous report covered but one, the JN-4H. In addition to the air speed, acceleration, and control positions as given in report no. 154, information is here given regarding the distance run and the ground speed for the various airplanes during the two maneuvers.
    Type: NACA-TR-249
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  • 29
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    Tests on thirteen navy type model propellers (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests on these model propellers were undertaken for the purpose of determining the performance coefficients and characteristics for certain selected series of propellers of form and type as commonly used in recent navy designs. The first series includes seven propellers of pitch ratio varying by 0.10 to 1.10, the area, form of blade, thickness, etc., representing an arbitrary standard propeller which had shown good results. The second series covers changes in thickness of blade section, other things equal, and the third series, changes in blade area, other things equal. These models are all of 36-inch diameter. Propellers A to G form the series on pitch ratio, C, N. I. J the series on thickness of section, and K, M, C, L the series on area. (author)
    Type: NACA-TR-237
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  • 30
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    Interaction Between Air Propellers and Airplane Structures (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this investigation was the determination of the character and amount of interaction between air propellers as usually mounted on airplanes and the adjacent parts of the airplane structure - or, more specifically, those parts of the airplane structure within the wash of the propeller, and capable of producing any significant effect on propeller performance. In report no. 177 such interaction between air propellers and certain simple geometrical forms was made the subject of investigation and report. The present investigation aims to carry this general study one stage further by substituting actual airplane structures for the simple geometrical forms. From the point of view of the present investigation, the airplane structures, viewed as an obstruction in the wake of the propeller, must also be viewed as a necessary part of the airplane and not as an appendage which might be installed or removed at will. (author)
    Type: NACA-TR-235
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  • 31
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    Tests on airplane fuselages, floats and hulls (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is a compilation of test data on airplane fuselages, nacelles, airship cars, seaplane floats, and seaplane hulls, prepared by the Bureau of Aeronautics, at the requests of the National Advisory Committee for Aeronautics. The discussion of the data includes the derivation of a scale correction curve to be used in obtaining the full scale drag. Composite curves of drag and L/D for floats and hulls are also given. (author)
    Type: NACA-TR-236
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  • 32
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    The aerodynamic characteristics of seven frequently used wing sections at full Reynolds number (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the aerodynamic properties of the wing sections U.S.A. 5, U.S.A. 27, U.S.A. 35 A, U.S.A. 35 B, Clark Y, R.A.F. 15, and Gottingen 387, as determined at various Reynolds numbers up to an approximately full scale value in the variable density wind tunnel of the National Advisory Committee for Aeronautics. It is shown that the characteristics of the wings investigated are affected greatly and in a somewhat erratic manner by variation of the Reynolds number. In general there is a small increase in maximum lift and an appreciable decrease in drag at all lifts.
    Type: NACA-TR-233
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  • 33
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    Approximations for column effect in airplane wing spars (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The significance attaching to "column effect" in airplane wing spars has been increasingly realized with the passage of time, but exact computations of the corrections to bending moment curves resulting from the existence of end loads are frequently omitted because of the additional labor involved in an analysis by rigorously correct methods. The present report represents an attempt to provide for approximate column effect corrections that can be graphically or otherwise expressed so as to be applied with a minimum of labor. Curves are plotted giving approximate values of the correction factors for single and two bay trusses of varying proportions and with various relationships between axial and lateral loads. It is further shown from an analysis of those curves that rough but useful approximations can be obtained from Perry's formula for corrected bending moment, with the assumed distance between points of inflection arbitrarily modified in accordance with rules given in the report. The discussion of general rules of variation of bending stress with axial load is accompanied by a study of the best distribution of the points of support along a spar for various conditions of loading.
    Type: NACA-TR-251
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  • 34
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    Savoia seaplane S.55 : military or commercial (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The S.55 is a two engine twin hull seaplane built by Societa Idrovolanti Alta Italia (Seaplane Company of Upper Italy). The S.55 (Santa Maria) is to be used for an around the world flight In 1927. It will have a useful load of 7,500 lbs. and a cruising speed of 100 MPH.
    Type: NACA-AC-33
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  • 35
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    Vojenska-Smolik S.16 airplane : all-metal long-distance observation bi-plane (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-34
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  • 36
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    Macchi M. 39 Seaplane: Single-Seat Racer with an 800 HP. Fiat "A-S2" Engine (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The M. 39 was designed by Castoldi to compete in the Schneider Cup Race of 1926 (Norfolk, VA). It is a monoplane with engine mounted in the fuselage, resting on two wing and hull mounted floats.
    Type: NACA-AC-32
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  • 37
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    Dornier "Superwal" commercial seaplane with : two Rolls-Royce "Condor" 600 HP. engines (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In November 1926, an exhibition flight of the Dornier giant flying boat was made for 3/4 of an hour. It was a larger version of the Dornier Wal, with a stepped hull, and wing stubs for lateral stability. It has a range of 1200 miles and is outfitted for baggage and 8 passengers.
    Type: NACA-AC-31
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  • 38
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    The "Dornier Mercury" commercial airplane with B.M.W. VI 600 HP. engine (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Dornier Mercury (Merkur) is an outgrowth of the Dornier Komet. It is designed as a passenger aircraft with the Alpine routes in mind. Its fuselage is made of steel for high stressed parts and duraluminum for all others. It can also be outfitted as a seaplane.
    Type: NACA-AC-30
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  • 39
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    Nieuport-Delage Pursuit Airplane 48 C. 1. : "jockey" type (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is a light single-seat pursuit airplane with a tractor propeller actuated by a 12 cylinder V-type Hispano-Suiza engine giving 400 HP at 2000 R.P.M. This is a single winged aircraft capable of 273 km/h.
    Type: NACA-AC-29
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  • 40
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    Combat and bombing airplane, Amiot 120 B 3 (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Amiot 120 B 3 is designed as a French combat aircraft. It can accept a variety of engines, and is equipped with 2 machine guns as well as specialized bomb sights and other combat equipment.
    Type: NACA-AC-28
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  • 41
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    Dyle and Bacalan metal monoplane, D.B. 10 : night bomber - equipped with two 420 HP. Jupiter engines (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The D.B. 10 is manufactured of duraluminum and special high resistance steel. It can be used as a passenger aircraft or as a bomber.
    Type: NACA-AC-27
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  • 42
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    Precision of wing sections and consequent aerodynamic effects (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-255
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  • 43
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    Method of Correcting Wind Tunnel Data for Omitted Parts of Airplane Models (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel models do not have complete similarity to the full scale airplane. Part of the dissimilarity is due to the difference between the stationary model in the artificial wind stream of the tunnel and the moving airplane in still air. There are a number of other reasons for departing from exact geometrical similitude. For reasons of accuracy and economy, all minor parts of the full scale airplane, such as struts, wires, fittings, control horns and other parts whose scale corrections are large are removed from wind tunnel models. By omitting the minor parts of the airplane in the wind tunnel model and adding to the forces and moments of the model those omitted parts measured full scale and properly reduced, the scale effects of such parts disappear from the model data. Scale effects due to major parts of the airplane, particularly the fuselage and wings, can be corrected by omitting the propeller and making the surface of the model as smooth as possible, two further departures from geometrical similitude between model and full scale that add considerably to the accuracy and economy of model tests.
    Type: NACA-TN-254
    Format: application/pdf
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  • 44
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    The Distribution of Loads Between the Wings of a Biplane Having Decalage (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is known that in a biplane the load is not distributed equally between the wings. The presence of one wing will affect the lift characteristics of the other wings. A designer must know the total load that each wing carries in order that he may design an adequate structure. The purpose here is to determine the distribution of loads between the wings of a biplane at various angles of decalage, when the gap/chord ratio is one, and there is no stagger. The effective lift of each wing was first investigated, using the vortex theory, and later by wind tunnel experiments. The results are given in tabular form.
    Type: NACA-TN-269
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  • 45
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    Mass distribution and performance of free flight models (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note deals with the mass distribution and performance of free flight models. An airplane model which is to be used in free flight tests must be balanced dynamically as well as statically, e.g., it must not only have a given weight and the proper center of gravity but also a given ellipsoid of inertia. Equations which relate the motions of an airplane and its model are given. Neglecting scale effect, these equations may be used to predict the performance of an airplane, under the action of gravity alone, from data obtained in making dropping tests of a correctly balanced model.
    Type: NACA-TN-268
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  • 46
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    Pressure distribution on wing ribs of the VE-7 and TS airplanes in flight (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the first of a series of notes, each of which presents the complete results of pressure distribution tests made by the National Advisory Committee for Aeronautics, on single-wing ribs of the VE-7 and TS airplanes for a particular condition of flight. The level flight results are presented here in the form of curves and show the comparison between the pressure distribution over a representative thin wing, R.A.F.-15, and a moderately thick wing, U.S.A.-27, throughout the range of angle of attack.
    Type: NACA-TN-267
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  • 47
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    Airfoil Lift with Changing Angle of Attack (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests have been made in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics to determine the effects of pitching oscillations upon the lift of an airfoil. It has been found that the lift of an airfoil, while pitching, is usually less than that which would exist at the same angle of attack in the stationary condition, although exceptions may occur when the lift is small or if the angle of attack is being rapidly reduced. It is also shown that the behavior of a pitching airfoil may be qualitatively explained on the basis of accepted aerodynamic theory.
    Type: NACA-TN-266
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  • 48
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    A load factor formula (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The ultimate test of a load factor formula is experience. The chief advantages of a semi rational formula over arbitrary factors are that it fairs in between points of experience and it differentiates according to variables within a type. Structural failure of an airplane apparently safe according to the formula would call for a specific change in the formula. The best class of airplanes with which to check a load factor formula seems to be those which have experienced structural failure. Table I comprises a list of the airplanes which have experienced failure in flight traceable to the wing structure. The load factor by formula is observed to be greater than the designed strength in each case, without a single exception. Table II comprises the load factor by formula with the designed strength of a number of well-known service types. The formula indicates that by far the majority of these have ample structural strength. One case considered here in deriving a suitable formula is that of a heavy load carrier of large size and practically no reserve power.
    Type: NACA-TN-263
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  • 49
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    Tension experiments on diaphragm metals (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Strips of german silver, steel, copper, duralumin, nickel and brass were tested in tension in an apparatus in which the change in deflection with time was measured by means of an interferometer. This change in deflection with time caused by the application and removal of a load is defined as "drift" and "recovery," respectively. It was measured in the time interval from approximately 5 seconds to 5 hours after loading. The data are given in a series of graphs in which the drift and recovery are plotted against time. The proportional drift and recovery in five hours are given for a number of the tests, and in addition are shown graphically for nickel and steel.
    Type: NACA-TN-261
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  • 50
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    The installation and correction of compasses in airplanes (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The saving of time that results from flying across country on compass headings is beginning to be widely recognized. At the same time the general use of steel tube fuselages has made a knowledge of compass correction much more necessary than was the case when wooden fuselages were the rule. This paper has been prepared primarily for the benefit of the pilot who has never studied navigation and who does not desire to go into the subject more deeply than to be able to fly compass courses with confidence. It also contains material for the designer who wishes to install his compasses with the expectation that they may be accurately corrected.
    Type: NACA-TN-262
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  • 51
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    Wall interference in closed type wind tunnels (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of tests has been conducted by the National Advisory Committee for Aeronautics, in the variable density wind tunnel on several airfoils of different sizes and sections to determine the effect of tunnel wall interference and to determine a correction which can be applied to reduce the error caused thereby. The use of several empirical corrections was attempted with little success. The Prandtl theoretical correction gives the best results and its use is recommended for correcting closed wind tunnel results to conditions of free air.
    Type: NACA-TN-256
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  • 52
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    Study of open jet wind tunnel cones (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests have been made by the National Advisory Committee for Aeronautics on the air flow in an open jet wind tunnel with various sizes, shapes, and spacings of cones, and the flow studied by means of velocity and direction surveys in conjunction with flow pictures. It was found that for all combinations of cones tested the flow is essentially the same, consisting of an inner core of decreasing diameter having uniform velocity and direction, and a boundary layer of more or less turbulent air increasing in thickness with length of jet. The energy ratio of the tunnel was obtained for the different combinations of cones, and the spilling around the exit cone causing undesirable air currents in the experiment chamber was noted. An empirical formula is given for the design of cones having no appreciable spilling.
    Type: NACA-TN-260
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  • 53
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    "A L C L A D" A New Corrosion Resistant Aluminum Product (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Described here is a new corrosion resistant aluminum product which is markedly superior to the present strong alloys. Its use should result in greatly increased life of a structural part. Alclad is a heat-treated aluminum, copper, manganese, magnesium alloy that has the corrosion resistance of pure metal at the surface and the strength of the strong alloy underneath. Of particular importance is the thorough character of the union between the alloy and the pure aluminum. Preliminary results of salt spray tests (24 weeks of exposure) show changes in tensile strength and elongation of Alclad 17ST, when any occurred, to be so small as to be well within the limits of experimental error. Some surface corrosion of the pure metal had taken place, but not enough to cause the specimens to break through those areas.
    Type: NACA-TN-259
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  • 54
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    A warning concerning the take-off with heavy load (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A successful take-off can be made with an airplane so heavily loaded that it cannot climb to a height greater than the span of its wings. The explanation is that the power required to maintain level flight at an altitude of the order of the wing span may be as much as 50 per cent greater than that necessary when the airplane is just clear of the ground. The failure of heavily loaded airplanes to continue climbing at the rate attained immediately after the actual take-off is a grave hazard and has resulted in great risk or catastrophe in three notable cases which are cited.
    Type: NACA-TN-258
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  • 55
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    Technical Preparation of the Airplane "Spirit of St. Louis." (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Given here is a brief history of the design and construction of the "Spirit of St. Lewis", the airplane that Charles Lindbergh flew solo across the Atlantic. Although the plan was to modify a standard model Ryan M-2, it was quickly determined that modification was less practical than redesign. Colonel Lindbergh's active participation in the design of the aircraft is noted. Given here are the general dimensions, specifications, weight characteristics, and man hours required to build the aircraft.
    Type: NACA-TN-257
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  • 56
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    Tests of the N.P.L. airship models in the variable density wind tunnel (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-264
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  • 57
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    Characteristics of a twin-float seaplane during take-off (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation of the planing and get-away characteristics of three representative types of seaplanes, namely, single float, boat, and twin float. The experiments carried out on the single float and boat types have been reported on previously. This report covers the investigation conducted on the twin-float seaplane, the DT-2, and includes as an appendix, a brief summary of the results obtained on all three tests. At low-water speeds, 20 to 30 miles per hour, the seaplane trims by the stern and has a high resistance. Above these speeds the longitudinal control becomes increasingly effective until, with corresponding speeds of 56 to 46 miles per hour. It was further determined that an increase in the load caused little if any change in the water speed at which the maximum angle and resistance occurred, but that it did produce an increase in the maximum angle.
    Type: NACA-TR-242
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  • 58
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    The Direct Measurement of Engine Power on an Airplane in Flight with a Hub Type Dynamometer (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests made to obtain direct measurements of engine power in flight. Tests were made with a Bendemann hub dynamometer installed on a modified DH-4 Airplane, Liberty 12 Engine, to determine the suitability of this apparatus. This dynamometer unit, which was designed specially for use with a liberty 12 engine, is a special propeller hub in which is incorporated a system of pistons and cylinders interposed between the propeller and the engine crankshaft. The torque and thrust forces are balanced by fluid pressures, which are recorded by instruments in the cockpit. These tests have shown the suitability of this type of hub dynamometer for measurement of power in flight and for the determination of the torque and power coefficients of the propeller. (author)
    Type: NACA-TR-252
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  • 59
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    Flow and Drag Formulas for Simple Quadrics (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives the pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. For the cases treated the concordance of theory and measurement is so close as to make a resume of results desirable. Incidentally formulas for the velocity at all points of the flow field are given, some being new forms for ready use derived in a previous paper. (author)
    Keywords: Aerodynamics
    Type: NACA-TR-253
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  • 60
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    Aerodynamic characteristics of airfoils IV : continuation of reports nos. 93, 124, and 182 (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This collection of data on airfoils has been made from the published reports of a number of the leading Aerodynamic Laboratories of this country and Europe. The information which was originally expressed according to the different customs of the several laboratories is here presented in a uniform series of charts and tables suitable for the use of designing engineers and for purposes of general reference. The authority for the results here presented is given as the name of the laboratory at which the experiments were conducted, with the size of the model, wind velocity, and year of test.
    Type: NACA-TR-244
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  • 61
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    A Preliminary Study of Fuel Injection and Compression Ignition as Applied to an Aircraft Engine Cylinder (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report summarizes some results obtained with a single cylinder test engine at the Langley Field Laboratory during a preliminary investigation of the problem of applying fuel injection and compression ignition to aircraft engines. For this work a standard Liberty Engine cylinder was fitted with a high compression, 11.4 : 1 compression ratio, piston, and equipped with an airless injection system, including a primary fuel pump, an injection pump, and an automatic injection valve. The results obtained during this investigation have indicated the possibility of applying airless injection and compression ignition to a cylinder of this size, 8-inch bore by 7-inch stroke, when operating at engine speeds as high as 1,850 R. P. M. A minimum specific fuel consumption with diesel engine fuel oil of 0.30 pound per I. HP. Hour was obtained when developing about 16 B. HP. At 1,730 R. P. M.
    Type: NACA-TR-243
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  • 62
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    The Corrosion of Magnesium and of the Magnesium Aluminum Alloys Containing Manganese (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The extensive use of magnesium and its alloys in aircraft has been seriously handicapped by the uncertainties surrounding their resistance to corrosion. This problem has been given intense study by the American Magnesium Corporation and at the request of the Subcommittee on Materials for Aircraft of the National Advisory Committee for Aeronautics this report was prepared on the corrosion of magnesium. The tentative conclusions drawn from the experimental facts of this investigation are as follows: the overvoltage of pure magnesium is quite high. On immersion in salt water the metal corrodes with the liberation of hydrogen until the film of corrosion product lowers the potential to a critical value. When the potential reaches this value it no longer exceeds the theoretical hydrogen potential plus the overvoltage of the metal. Rapid corrosion consequently ceases. When aluminum is added, especially when in large amounts, the overvoltage is decreased and hydrogen plates out at a much lower potential than with pure magnesium. The addition of small amount of manganese raises the overvoltage back to practically that of pure metal, and the film is again negative.
    Type: NACA-TR-248
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  • 63
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    Distribution of Pressure Over Model of the Upper Wing and Aileron of a Fokker D-VII Airplane (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests made for the purpose of determining the distribution of pressure over a model of the tapered portion of the upper wing and the aileron of a Fokker D-VII Airplane. Normal pressures were measured simultaneously at 74 points distributed over the wing and aileron. Tests were made throughout the useful range of angles of attack with aileron setting ranging from -20 degrees to +20 degrees. The results are presented graphically. It was found that the pressure distribution along the chord is in general similar to that of thick tapered airfoils previously tested. The maximum resultant pressure recorded was five times the dynamic pressure. The distribution of the air load along the span may be assumed to be uniform for design purposes. Aileron displacements affect the pressures forward to the leading edge of the wing and may increase the air load on the outer portion of the wing by a considerable amount. With the wing at large angles of attack, the overhanging portion of the aileron creates usually a burble flow and therefore a large drag. The balance reduces the control stick forces at small angles of attack for all aileron displacements. At large angles of attack it does this for small displacements only. With the airplane at its maximum speed, an angle of attack of 18 degrees, and a down aileron displacement of 20 degrees, the bending moment tending to break off the overhanging portion of the aileron will be greater than that caused by a uniform static load of 35 pounds per square foot.
    Type: NACA-TR-254
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  • 64
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    Nomenclature for Aeronautics (1927)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: This nomenclature for aeronautics was prepared by a Special Conference on Aeronautical Nomenclature by the executive committee of the National Advisory Committee for Aeronautics at a meeting held on August 19, 1924, at which meeting Dr. Joseph S. Ames was appointed chairman of the conference. The conference was composed of representatives of the National Advisory Committee for Aeronautics and specially appointed representatives officially designated by the Army Air Service, the Bureau of Aeronautics of the Navy Department, the Bureau of Standards, the American Society of Mechanical Engineers, the Society of Automotive Engineers, and the Aeronautical Chamber of Commerce. The purpose of the committee in the preparation and publication of this report is to secure uniformity in the official documents of the government and, as far as possible, in technical and other commercial publications
    Type: NACA-TR-240
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  • 65
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    Tables for calibrating altimeters and computing altitudes based on the standard atmosphere (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During 1925 the assumption of an isothermal atmosphere which was in general use as the standard for the calibration of altimeters in the United States was replaced by a standard atmosphere which assumes an altitude-temperature relation closely corresponding to the average of upper air observations at latitude 40 degrees in this country. The same standard atmosphere had already been adopted somewhat earlier in the United States as the aircraft performance standard. National Advisory Committee for Aeronautics Technical Reports nos. 147 and 218 give necessary constants, tables, and information. However, neither of these reports includes all of the tables required for the computation of actual altitudes nor those readily suitable for use in calibrating altimeters, since the altitude intervals for which data are given are not sufficiently small. The present report has been prepared specifically for these purposes. The formulas which define the standard atmosphere are given in this report, together with other formulas giving the corrections to be applied to the standard altitude in order to obtain the actual altitude when the necessary observations of pressure and temperature are available. The tables necessary for the use of this standard atmosphere in calibrating altimeters and in computing altitudes form the principal part of this report. An example of the computation of actual altitudes from observed pressures and temperatures are given in table IV.
    Type: NACA-TR-246
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  • 66
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    The effect of flight path inclination on airplane velocity (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report was prepared at the request of the National Advisory Committee for Aeronautics in order to supply a systematic study of the relations between the flight velocity V and its horizontal component V subscript H, in power glides. Curves of V and V subscript H plotted against the inclination of the flight path 0 are given, together with curves which show the maximum values of V subscript H and the corresponding values of 0. Curves are also given showing the effect of small departures from the horizontal in high speed performance testing.
    Type: NACA-TR-238
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  • 67
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    Power Output and Air Requirements of a Two-stroke Cycle Engine for Aeronautical Use (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was undertaken to determine the pressure and amount of air necessary for satisfactory high-speed, two-stroke cycle operation and thus permit the power requirements of the air pump or blower to be determined. Based on power output and air requirement here obtained the two-stroke cycle engine would seem to be favorable for aeronautical use. No attempts were made to secure satisfactory operation at idling speeds.
    Type: NACA-TR-239
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  • 68
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    Annual report for the National Advisory Committee for Aeronautics (12th).administrative report including Technical Reports nos. 233 to 256 (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Type: NACA-AR-12
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  • 69
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    The air forces on a systematic series of biplane and triplane cellule models (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The air forces on a systematic series of biplane and triplane cellule models are the subject of this report. The test consist in the determination of the lift, drag, and moment of each individual airfoil in each cellule, mostly with the same wing section. The magnitude of the gap and of the stagger is systematically varied; not, however, the decalage, which is zero throughout the tests. Certain check tests with a second wing section make the tests more complete and conclusions more convincing. The results give evidence that the present army and navy specifications for the relative lifts of biplanes are good. They furnish material for improving such specifications for the relative lifts of triplanes. A larger number of factors can now be prescribed to take care of different cases.
    Type: NACA-TR-256
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  • 70
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    Description of the NACA Universal Test Engine and Some Test Results (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the 5-inch bore by 7-inch stroke single cylinder test engine used at the Langley Field Laboratory of the National Advisory Committee for Aeronautics in laboratory research on internal-combustion engine problems and presents some results of tests made therewith. The engine is arranged for variation over wide ranges, of the compression ratio and lift and timing of both inlet and exhaust valves while the engine is in operation. Provision is also made for the connection of a number of auxiliaries. These features tend to make the engine universal in character, and especially suited for the study of certain problems involving change in compression ratio, valve timing, and lift.
    Type: NACA-TR-250
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  • 71
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    Meteorological conditions along airways (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is an attempt to show the kind of meteorological information that is needed, and is in part available, for the purpose of determining operating conditions along airways. In general, the same factors affect these operating conditions along all airways though in varying degree, depending upon their topographic, geographic, and other characteristics; but in order to bring out as clearly as possible the nature of the data available, a specific example is taken, that of the Chicago-Dallas airway on which regular flying begins this year (1926).
    Type: NACA-TR-245
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  • 72
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    Pressure of air on coming to rest from various speeds (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The text gives theoretical formulas from which is computed a table for the pressure of air on coming to rest from various speeds, such as those of aircraft and propeller blades. Pressure graphs are given for speeds from 1 cm. Sec. up to those of swift projectiles.
    Type: NACA-TR-247
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  • 73
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    Electrical characteristics of spark generators for automotive ignition (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper reports the results of an extensive program of measurements on 11 ignition systems differing widely in type. The results serve primarily to give representative data on the electric and magnetic constants of such systems, and on the secondary voltage produced by them under various conditions of speed, timing, shunting resistance, etc. They also serve to confirm certain of the theoretical formulas which have been proposed to connect the performance of such systems with their electrical constants, and to indicate the extent to which certain simplified model circuits duplicate the performance of the actual apparatus.
    Type: NACA-TR-241
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  • 74
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    Three methods of calculating range and endurance of airplanes (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report develops new equations which give the range and endurance of airplanes with an accuracy equal to that obtained from a step-by-step integration of the flight. A method of obtaining equally satisfactory results from Brequet's equations is also given in detail. A third method of calculating range and endurance, derived by the writer for use in routine estimating in the Bureau of Aeronautics, is also given in full. The reports contains tables and curves arranged for convenient use and illustrates the three methods by comparative estimates.
    Type: NACA-TR-234
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  • 75
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    Experiments on airfoils with aileron and slot (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report contains the results of a few experiments on three airfoils to which the rear portions, having chords respectively 1/4, 1/3, and 2/5 of the total chords, are hinged so as to form ailerons, especial attention being given to the shape of the slot between the aileron and the main portion of the aileron.
    Type: NACA-TM-437
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  • 76
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    Structural details of German gliders (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The structural details such as wings, fuselage, landing gear, and steering organs of German gliders are detailed in this report.
    Type: NACA-TM-439
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  • 77
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    Duralumin - Defects and Failures (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is proposed in this paper to identify some of the defects and failures in duralumin most frequently encountered by the aircraft industry with a view to indicate their importance. The defects and failures in duralumin may be classified into the following groups: 1) defects produced during manufacture; 2) defects produced during fabrication; 3) corrosion and erosion; and 4) fatigue failures. Only the first two will be covered in this report.
    Type: NACA-TM-443
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  • 78
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    "Gloster" high lift biplane wings (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The main object of these wings was to obtain a high lift without increasing the total drag, and the idea was conceived that, by using a deep high-lift section for the top wing and a medium section for the bottom wing, the mutual interference between the two would be such as to give greater efficiency of the combination as compared with two wings of equal section.
    Type: NACA-TM-442
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  • 79
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    Metal Aircraft Construction at Vickers : Some Interesting New Forms Developed (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains descriptions of construction techniques at the Vickers plant including the building of the "wandering web," the spar flange, and the Vickers spars.
    Type: NACA-TM-440
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  • 80
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    Safety in airplane flight (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents methods to reduce the incidence of aviation accidents. Some of the methods discussed include enlistment and training of aviators, improvement of controls and control surfaces, and upgrading of power plants.
    Type: NACA-TM-438
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  • 81
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    Calculating thrust distribution and efficiency of air propellers (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: I am now proposing a method for the preliminary approximate calculation of the thrust distribution and efficiency of air propellers under any operating conditions. Our task becomes the following, namely, to determine the speed relations and the forces developed on a section with a given direction and velocity of the air current, a problem which can be solved with the aid of the momentum theory.
    Type: NACA-TM-444
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  • 82
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    Increasing Lift by Releasing Compressed Air on Suction Side of Airfoil (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation was limited chiefly to the region of high angles of attack since it is only in this region that any considerable change in the character of the flow can be expected from such artificial aids. The slot, through which compressed air was blown, was formed by two pieces of sheet steel connected by screws at intervals of about 5 cm. It was intended to regulate the width of the slot by means of these screws. Much more compressed air was required than was originally supposed, hence all the delivery pipes were much too small. This experiment, therefore, is to be regarded as only a preliminary one.
    Type: NACA-TM-441
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  • 83
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    Turbulent flow (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-435 , International Congress for Applied Mechanics ( 1926: Zurich, Switzerland).
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  • 84
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    Approximation method for determining the static stability of a monoplane glider (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The calculations in this paper afford an approximate solution of the static stability. A derivation of the formulas for moment coefficient of a wing, moment coefficient of elevator, and the total moment of the combined wing and elevator and the moment coefficient with reference to the center of gravity are provided.
    Type: NACA-TM-436
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  • 85
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    Slotted-Wing Airplanes (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Different applications of the slotted-wing principle are discussed as well as the advantages of using them.
    Type: NACA-TM-432
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  • 86
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    Glider construction and design (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The endeavor to draw a strict line between gliders and soarers as been recently abandoned and the following classification adopted: 1) gliders controlled by shifting the weight of the body; 2) gliders controlled by rudders; 3) gliders controlled by wings. The different classes are discussed as well as materials and parts used in construction.
    Type: NACA-TM-434
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  • 87
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    Drag measurements on a Junkers wing section : application of the Betz Method to the results of comparative tests made on a model and on an airplane in flight (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The comparison of model tests in flight can be based on the result of such measurements. They are very important from the aerodynamical point of view, as they lead to useful conclusions regarding the behavior of the wing, its best shape and the conformity of theoretical and actual flow. Although there still remains a certain prejudice against such measurements, I have still attempted to make these comparative tests in order to inspire confidence in their reliability.
    Type: NACA-TM-428
    Format: application/pdf
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  • 88
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    Seaplanes floats and hulls. Part I (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This part of the report presents characteristics and graphic representations of water resistance. The laws of similarity are discussed as well as the theory of model tests. The test procedures and model tests of other countries are also discussed.
    Type: NACA-TM-426
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  • 89
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    Seaplanes Floats and Hulls. Part II (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Different float designs are presented and the investigations are discussed.
    Type: NACA-TM-427
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  • 90
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    Some German gliders of 1920-1923 (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-433
    Format: application/pdf
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  • 91
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    Recent suggestions in Diesel-engine construction (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Different methods for increasing the efficiency of diesel engines are presented and some new designs are given.
    Type: NACA-TM-425
    Format: application/pdf
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  • 92
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    Building a full-size glider (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The building and flying of a glider is possible for anyone who can use a few basic tools. This report presents some plans and techniques for building your own glider.
    Type: NACA-TM-429
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  • 93
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    Discussion of the results of the boundary-layer tests of an airfoil fitted with a rotary cylinder (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of the velocity measurements in the boundary layer described in NACA-TM 411 are here discussed in greater detail. The measurements made were of the velocity distribution in the vicinity of an airfoil model fitted with a rotary cylinder and were undertaken for the purpose of obtaining a closer insight into the phenomena observed in experimenting with this model.
    Type: NACA-TM-424
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  • 94
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    Lindbergh's flight (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-423
    Format: application/pdf
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  • 95
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    Aero dopes and varnishes (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Before proceeding to discuss the preparation of dope solutions, it will be necessary to consider some of the essential properties which should be possessed of a dope film, deposited in and on the surface of an aero fabric. The first is that it should tighten the material and second it should withstand weathering.
    Type: NACA-TM-421
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  • 96
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    Effects of roughness on airfoils (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: We will here report on the effects of coarsely roughening not only the pressure side but also the suction or upper side of airfoils, as the first group of a larger series of experiments.
    Type: NACA-TM-430
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  • 97
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    Some Notes on Gasoline-Engine Development (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments were carried out using a special engine with small glass windows and a stroboscope to record various aspects of engine performance. Valve position, supercharging, and torque recoil were all investigated with this experimental apparatus.
    Type: NACA-TM-420
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  • 98
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    Experiments on airfoils with trailing edge cut away (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Airfoils with their trailing edge cut away are often found on aircraft, as the fins on the hulls of flying boats and the central section of the wings for affording better visibility. It was therefore of some interest to discover the effect of such cutaways on the lift and drag and on the position of the center of pressure. For this purpose, systematic experiments were performed on two different airfoils, a symmetrical airfoil and an airfoil of medium thickness, with successive shortenings of their chords.
    Type: NACA-TM-431
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  • 99
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    Experiments with three horizontal empennages (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The main objective of these experiments was to determine how the air forces on the whole empennage are affected by varying the size of the elevator without changing the size of the whole empennage. The secondary objective was to determine how the magnitude of the air forces acting on the elevator (or the elevator moments) are affected by varying the angle of attack of the whole empennage, or of the elevator alone.
    Type: NACA-TM-419
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  • 100
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    Investigation of a wing with an auxiliary upper part (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents experiments in which two parts of the wing were arranged so as to form a biplane, which was subjected to normal three-component measurements, the two parts being placed in various relative positions with respect to the gap a and the stagger b.
    Type: NACA-TM-418
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