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  • Maps  (8)
  • Other Sources  (160)
  • 2005-2009
  • 1930-1934  (168)
  • 1933  (168)
  • 1
    Map available for loan
    Map available for loan
    Assumar; 33-A. (1919-1978)
    Associated volumes
    Details Availability
    Call number: K 1979.9440(33-A) / R13
    In: Carta geológica de Portugal
    Type of Medium: Map available for loan
    Pages: 1 Kt., gefaltet + Er.-H. (37 S.)
    Location: Upper compact magazine
    Branch Library: GFZ Library
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  • 2
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    Tilting due to glacial melting (1933)
    In:  The Journal of Geology, Milano, Gustav Fischer, vol. 41, no. 3, pp. 449-467, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Über Erdbeben mit Herdtiefen von mehreren hundert Kilometern (1933)
    In:  Geologische Rundschau, Milano, Gustav Fischer, vol. 24, no. 3, pp. 227-239, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Seismology ; Hypocentral depth ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Re suggestion by Dr. Harold Jeffreys regarding P(bar) and Pg (1933)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 40, no. 3, pp. 97-98, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Seismology ; P-waves ; CRUST
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Is present tilting in North America due to glacial melting ? (1933)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 44, no. 3, pp. 152-153, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Advantages of using geocentric latitude in calculating distances (1933)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 40, no. 3, pp. 380-389, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: mathematics ; geometry ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Experiments testing seismographic methods for determining crustal structure (1933)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 44, no. 3, pp. 170-171, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; Velocity depth profile
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Erde (physikalische Beschaffenheit) (1933)
    Gustav Fischer
    In:  Professional Paper, Handwörterbuch der Naturwissenschaften Bd. 3, Jena, Gustav Fischer, vol. 3, no. VIIa, pp. 762-774, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1933
    Keywords: Handbook of geophysics ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Dürrezahlen, ein Versuch, die Auswirkungen von Dürreperioden klimastatistisch zu erfassen (1933)
    In:  Fortschritte der Landwirtschaft, 8: 313-316
    Details
    Publication Date: 1933
    Description: Beschreibung der Häufigkeitsverteilung von Trockenperioden durch Belegung und Gewichtung von niederschlagsfreien Tagen im Mittel von Dekaden KATASTER-BESCHREIBUNG: Betrachtung einzelner Dekaden, Vergleich der Häufigkeitsverteilung der Dürrezahlen, Schlussfolgerungen für die Gefährdung durch Dürre für die Landwirtschaft KATASTER-DETAIL: Delta Nied- (Dez-März), Hervortreten des Winters als Dürrezeit im Raum Wien
    Keywords: Utrecht, Wien ; 1851-1910, 1881-1920 ; Landwirtschaft ; Niederschlag ; Trockenheit
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    BIBLIOGRAPHY INKA BB
  • 10
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    Der Nonnenraupenfraß achtzehnhundertneunundachtzig / einundneunzig und der Wirbelsturm vom 14. Juli 1894 im Ebersbergerforst (1933)
    Details
    Publication Date: 1933
    Description: brauchbare Anekdote für Zwischenbericht INKA-BB KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
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  • 11
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    Hat das Wetter Einfluß auf den Eintritt des Todes? (1933)
    In:  Virchows Archiv für Pathologische Anatomie und Physiologie und für Klinische Medizin, v291 n1-2, 237-259
    Details
    Publication Date: 1933
    Description: statistische Bearbeitung von über 16.000 Berliner Sektionsfällen, Vergleich der täglichen Sterbeziffer mit der Wetterlage KATASTER-BESCHREIBUNG: Zunahme der Mortalität an Kaltfront- und Warmfronttagen KATASTER-DETAIL:
    Keywords: Berlin ; 1926-1928 ; Umweltmedizin ; Witterung
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    BIBLIOGRAPHY INKA BB
  • 12
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    Der Einfluß klimatischer Faktoren auf die Höhe des Pflanzenertrages (1933)
    In:  Vortrag, Schr. Königsberg. gel. Ges., Naturwiss. Kl., 10 H.6) Max Niemeyer, Halle a. S.:16
    Details
    Publication Date: 1933
    Description: Untersuchungen über den Einfluss klimatischer Wachstumsfaktoren auf den Ertrag KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenschein) auf den Ertrag KATASTER-DETAIL: Delta Luftdruck +, dann Erträge +; Delta O2-Gehalt (Luft) = 15 %, dann Ertrag = max; Delta CO2-Gehalt (Luft) = 0.03 %, dann Ertrag = max; Delta Lichtintensität - und Delta CO2-Gehalt +, dann Ertrag +; Delta T Boden, Vegetationszeit) + : Tmit 〉 5 °C, dann Ertrag; Delta Nied +, dann Ertrag +;
    Keywords: Königsberg, Preußen ; 1931-1932 ; Boden ; Ertrag ; Niederschlag ; Temperatur ; Wind ; Witterung ; Sonnenscheindauer
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  • 13
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    Der Maikäfer in Württemberg (1933)
    In:  Monographie; Reihe: Arbeit aus der Landesanstalt für Pflanzenschutz Hohenheim; Ulmer Verlag, Stuttgart; 140p.
    Details
    Publication Date: 1933
    Description: Das Auftreten des Maikäfers in Württemberg, sowie seine räumlich differenzierte Ausprägung wird in Abhängigkeit klimatischer und nicht-klimatischer Faktoren betrachtet. Eine detaillierte Karte hierzu ist enthalten. Entwicklungsdauer und Folgenzahl des Maikäfers werden als Funktion der Temperatur graphisch dargestellt; außer den Reinformen des 3- und 4-jährigen Zyklus werden noch Mischformen und ihr temperaturbedingt unterschiedliches Auftreten in Württemberg beleuchtet. KATASTER-BESCHREIBUNG: Entwicklungsgeschwindigkeit hängt von der Temp. ab (Bsp.: durch Temp.erhöhung im Warmhaus wurde die Fraßzeit um 4 Monate verlängert und folglich die Verpuppung um 5-6 Monate vorverlegt =〉 die Käfer verließen den Boden schon 1 Jahr früher als durch ihren Entwicklungszyklus normal gewesen wäre KATASTER-DETAIL:
    Keywords: Württemberg ; 1836-1928 ; Forst ; Pflanzenschädling
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  • 14
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    Beziehungen der Sommerwitterung im nördlichen Alpenvorland mit dem Vorwetter. III. Sommerwitterung und Ernteerträgnis (1933)
    In:  Meteorologische Zeitschrift 8:300-306.
    Details
    Publication Date: 1933
    Description: Korrelation zwischen Junitemperaturen und Hafererträgen Regressionsgleichung (Temperaturzunahme bedingt Ertragsrückgang) KATASTER-BESCHREIBUNG: Einfluss der Junitemperatur auf die Haferernte KATASTER-DETAIL: Delta T (Juni) +, dann Erträge --; Änderungen um +1°C, dann Verminderung der Erträge um ~2,1 Zentner; Änderungen um +5°C, dann Verminderung der Erträge um 10 Zentner pro 1 ha
    Keywords: Niederbayern und Oberösterreich ; 1885-1925 ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung
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  • 15
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    Witterung und Insekten in der Gegend von Rostock 1932 (1933)
    In:  Anzeig. Schädlingskunde 9; p.29-34
    Details
    Publication Date: 1933
    Description: Der Autor beschreibt Beobachtungen über verschiedene schädigende und nicht schädigende Insekten im Acker- und Obstbau, sowie der Forstwirtschaft und versucht ihre Ursachen im Wetter des Jahres 1932 zu finden. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Mecklenburg-Vorpommern ; 1932 ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung
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  • 16
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    Witterung und Insekten (1933)
    In:  Anzeig. Schädlingskunde 9; p.109-112
    Details
    Publication Date: 1933
    Description: Der Autor diskutiert im Bezug auf einen Artikel von Friederichs in der selben Zeitschrift den Zusammenhang zwischen Wetter bzw. Witterung und dem Auftreten von Insekten insbesondere Blattläusen und vergleicht diese mit eigenen Beobachtungen. Folgende Erkenntnisse erschließen sich aus seinen eigenen Beobachtungen: Im Frühjahr entwickeln sich Pflanzen auch wenn es kühl ist gut, Insekten dagegen weniger, wenn genug Licht zur Verfügung steht. Rolle der Feuchtigkeit (nicht zwangsweise als Niederschlag) wird hervorgehoben. Beständige Witterung ist für die Individuenzahl einer Insektenpopulation förderlich KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bergedorf ; 1932
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  • 17
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    Handbuch der Geophysik, Volume 7: Physik der Hydrosphäre (only 1. part), 5 + 252 S. (1933)
    Bornträger
    In:  Berlin, Bornträger, vol. 12, 189 S., no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1933
    Keywords: Handbook of geophysics ; oceanography
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    BIBLIOGRAPHY SEISMOLOGY
  • 18
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    Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-477
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    NASA TECHNICAL REPORTS
  • 19
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    Wind-tunnel tests on model wing with Fowler flap and specially developed leading-edge slot (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made in the NACA 7 by 10 foot wind tunnel to find the increase in maximum lift coefficient which could be obtained by providing a model wing with both a Fowler trailing-edge extension flap and a Handley Page type leading-edge slot. A conventional Handley page slot proportioned to operate on the plain wing without a flap gave but a slight increase with the flap; so a special form of slot was developed to work more effectively with the flap. With the best combined arrangement the maximum lift coefficient based on the original area was increased from 3.17, for the Fowler wing, to 3.62. The minimum drag coefficient with both devices retracted was increased in approximately the same proportion. Tests were also made with the special-type slot on the plain wing without the flap. The special slot, used either with or without the Fowler flap, gave definitely higher values of the maximum lift coefficient than the slots of conventional form, with an increase of the same order in the minimum drag coefficient.
    Type: NACA-TN-459
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  • 20
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    Development of the Rules Governing the Strength of Airplanes. Part I : German Loading Conditions up to 1926 (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Load factors and loading conditions are presented for German aircraft. Loading conditions under various stress factors are presented along with a breakdown of individual aircraft components such as landing gear, wings, etc.
    Type: NACA-TM-716
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    NASA TECHNICAL REPORTS
  • 21
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    Guide Vanes for Deflecting Fluid Currents with Small Loss of Energy (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The transverse momentum of the deflected air stream to be absorbed is divided between the intermediate and outside walls, so that the pressure increase on each wall is much smaller and the danger of separation is diminished. The formation of secondary vortices is also diminished. By taking as the basis profiles with high c(sub a), such as have proved practically favorable, it is not possible to find a satisfactory form of grid simply on the assumption that the flow is potential. The requirements called for the most uniform possible velocity distribution behind the bend and the smallest possible losses.
    Type: NACA-TM-722
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    NASA TECHNICAL REPORTS
  • 22
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    Attaining a steady air stream in wind tunnels (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Many experimental arrangements of varying kind involve the problems of assuring a large, steady air stream both as to volume and to time. For this reason a separate discussion of the methods by which this is achieved should prove of particular interest. Motors and blades receive special attention and a review of existent wind tunnels is also provided.
    Type: NACA-TM-726
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  • 23
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    Development of the rules governing the strength of airplanes. Part III : loading conditions in France, Italy, Holland, and Russia - aims at standardization (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The historical development of the rules for structural strength of aircraft in the leading countries is traced from the beginning of flight to date. The term "factor of safety" is critically analyzed; its replacement by probability considerations has been considered desirable.
    Type: NACA-TM-718
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    NASA TECHNICAL REPORTS
  • 24
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    Development of Air-cooled Engines with Blower Cooling (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: With the aid of a heating device, the heat transfer to cylinders with conical fins of various forms is determined both for shrouded and exposed cylinders. Simultaneously the pressure drop for overcoming the resistance to the motion of air between the fins of the enclosed cylinder is measured. Thus the relations between the heat transfer and the energy required for cooling are discovered. The investigations show that the heat transfer in a conducted air flow is much greater than in a free current and that further improvement, as compared with free exposure, is possible through narrower spaces between the fins.
    Type: NACA-TM-725
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    NASA TECHNICAL REPORTS
  • 25
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    Trend of airplane flight characteristics (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the development of airplane characteristics since the war and indicates the direction development should take in the immediate future. Some of the major topics include: the behavior of an airplane about its lateral, vertical, and longitudinal axes. Behavior at large angles of attack and landing characteristics are also included.
    Type: NACA-TM-731 , Deutsche Versuchsanstalt fur Luftfahrt ( 1932 : Berlin)
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  • 26
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    An Airfoil Spanning an Open Jet (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Proceeding from the fundamental problem on the mutual relation of a wing and free boundaries the distribution of the circulation is determined for an airfoil spanning an open jet of rectangular section at different aspect ratios, and then for an open jet of circular section. The solution is obtained by means of a Fourier series and computations have been performed for different values of the variables. The second part describes the experiments performed for the purpose of proving the theory. The results confirm the theory. In conclusion it defines the induced drag of a wing extending across an open jet and compares it with the drag of a monoplane having a span equal to the jet width at equal total lift.
    Type: NACA-TM-723
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  • 27
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    The flight of an autogiro at high speed (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a method for computing the flight performance of an autogiro at high speed, the velocity component along the blades being accounted for by calculation of the profile drag and the equation for zero torque.
    Type: NACA-TM-729
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  • 28
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    Wind-tunnel research comparing lateral control devices, particularly at high angles of attack III : ordinary ailerons rigged up 10 degrees when neutral (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind-tunnel tests made on three model wings having different sizes of ordinary ailerons rigged up 10 degrees when neutral, the same models having previously been tested with the ailerons rigged even with the wings in the usual manner. One of the wings had ailerons of medium size, 25 per cent of the wing chord by 40 per cent of the semispan, one had long, narrow ailerons, and one had short, wide ones. These tests are part of a general investigation on lateral control devices, with particular reference to the control at high angles of attack, in which all the devices are being subjected to the same series of tests in the 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics. Force tests of the usual type, free-autorotation tests, and forced-rotation tests were made showing the effect of the ailerons on the general performance of the wing, on the lateral controllability, and on the lateral stability.
    Type: NACA-TR-423
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  • 29
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    Wind-tunnel research comparing lateral control devices, particularly at high angles of attack I : ordinary ailerons on rectangular wings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the first in a series in which it is intended to compare the relative merits of all ordinary and some special forms of ailerons and other lateral control devices in regard to their effect on lateral controllability, lateral stability, and airplane performance. The comparisons are based on wind-tunnel test data, all the control devices being fitted to model wings having the same span, area, and airfoil section, and being subjected to the same series of force and rotation tests. The results are given for five different aileron movements: one with equal up-and-down deflection, one with average and one with extreme differential motion, one with upward deflection only, and one with the ailerons arranged to float with respect to the wing.
    Type: NACA-TR-419
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  • 30
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    Theory of wing sections of arbitrary shape (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a solution of the problem of the theoretical flow of a frictionless incompressible fluid past airfoils of arbitrary forms. The velocity of the 2-dimensional flow is explicitly expressed for any point of the surface, and for any orientation, by an exact expression containing a number of parameters which are functions of the form only and which may be evaluated by convenient graphical methods. The method is particularly simple and convenient for bodies of streamline forms. The results have been applied to typical airfoils and compared with experimental data.
    Type: NACA-TR-411
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  • 31
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    Measurements of Flow in the Boundary Layer of a 1/40-Scale Model of the U. S. Airship "Akron." (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of measurements of flow in the boundary layer of a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4) made with the object of determining the boundary-layer thickness, the point of transition from laminar to the turbulent flow, and the velocity distribution in the boundary layer.
    Type: NACA-TR-430
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  • 32
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    Rates of fuel discharge as affected by the design of fuel-injection systems for internal-combustion engines (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Using the method of weighing fuel collected in a receiver during a definite interval of the injection period, rates of discharge were determined, and the effects noted, when various changes were made in a fuel-injection system. The injection system consisted primarily of a by-pass controlled fuel pump and an automatic injection valve. The variables of the system studied were the pump speed, pump-throttle setting, discharge-orifice diameter, injection-valve opening and closing pressures, and injection-tube length and diameter.
    Type: NACA-TR-433
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  • 33
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    Wind-tunnel tests of a Clark Y wing with a narrow auxiliary airfoil in different positions (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests were made on a combination of a Clark Y wing and a narrow auxiliary airfoil to find the best location of the auxiliary airfoil with respect to the main wing. The auxiliary was a highly cambered airfoil of medium thickness having a chord 14.5 per cent that of the main wing. It was tested in 141 different positions ahead of, above, and behind the nose portion of the main wing, the range of the test points being extended until the best aerodynamic conditions were covered. A range of positions was found in which the combination of main wing and auxiliary gave substantially greater aerodynamic efficiency and higher maximum lift coefficients (based on total area) than the main Clark Y wing alone. In the optimum position tested, considering both the maximum lift and the speed-range ratio, the combination of main wing and auxiliary gave an increase in the maximum lift coefficient of 32 per cent together with an increase in the ratio of 21 per cent of the respective values for the main Clark Y wing alone.
    Type: NACA-TR-428
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  • 34
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    The effect of multiple fixed slots and a trailing-edge flap on the lift and drag of a Clark Y airfoil (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Lift and drag tests were made on a Clark Y wing equipped with four fixed slots and a trailing-edge flap in the 5-foot vertical wind tunnel of the National Advisory Committee for Aeronautics. All possible combinations of the four slots were tested with the flap neutral and the most promising combinations were tested with the flap down 45 degrees. Considering both the maximum lift coefficient and the speed-range ratio with the flap neutral no appreciable improvement was found with the use of more than the single leading-edge slot. With the flap down 45 degrees a maximum lift coefficient of 2.60 was obtained but the particular slot combination used had a rather large minimum drag coefficient with the flap neutral. With the flap down 45 degrees the optimum combination, considering both the maximum lift coefficient and the speed-range ratio, was obtained with only the two rearmost slots in use. For this arrangement the maximum lift coefficient was 2.44.
    Type: NACA-TR-427
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  • 35
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    The 7 by 10 Foot Wind Tunnel of the National Advisory Committee for Aeronautics (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
    Type: NACA-TR-412
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  • 36
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    The Elimination of Fire Hazard Due to Back Fires (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A critical study was made of the operation of a type of back-fire arrester used to reduce the fire hazard of aircraft engines. A flame arrester consisting of a pack or plug of alternate flat and corrugated plates of thin metal was installed in the intake pipe of a gasoline engines; an auxiliary spark plug inserted in the intake manifold permitted the production of artificial back fires at will. It was found possible to design a plug which prevented all back fires from reaching the carburetor.
    Type: NACA-TR-409
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  • 37
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    Drop and Flight Tests on NY-2 Landing Gears Including Measurements of Vertical Velocities at Landing (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to obtain quantitative information on the effectiveness of three landing gears for the NY-2 (consolidated training) airplane. The investigation consisted of static, drop, and flight tests on landing gears of the oleo-rubber-disk and the mercury rubber-chord types, and flight tests only on a landing gear of the conventional split-axle rubber-cord type. The results show that the oleo gear is the most effective of the three landing gears in minimizing impact forces and in dissipating the energy taken.
    Type: NACA-TR-406
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  • 38
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    General formulas and charts for the calculation of airplane performance (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents general formulas for the determination of all major airplane performance characteristics. A rigorous analysis is used, making no assumption regarding the attitude of the airplane at which maximum rate of climb occurs, but finding the attitude at which the excess thrust horsepower is maximum. Equations and charts are developed which show the variation of performance due to a change in any of the customary design parameters. Performance determination by use of the formulas and charts is rapid and explicit. The results obtained by this performance method have been found to give agreement with flight tests that is, in general, equal or superior to results obtained by present commonly used methods.
    Type: NACA-TR-408
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  • 39
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    Heinkel HE 70 commercial airplane (German) : a seven-seat cantilever low-wing monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-183
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  • 40
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    The Dewoitine D.500 pursuit airplane (French) : an all-metal cantilever low-wing monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-180
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  • 41
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    The Shackleton-Murray SM-1 light airplane : a two-place high-wing monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-181
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  • 42
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    Charts for determining the pitching moment of tapered wings with sweepback and twist (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a convenient method for calculating the pitching-moment characteristics of tapered wings with sweepback and twist. The method is based on the fact that the pitching-moment characteristics of a wing may be specified by giving the value of the pitching moment at zero lift and the location of the axis about which the axis is constant. Data for calculating these characteristics are presented by curves which apply to wings having a linear distribution of twist along the span and which cover a large range of aspect ratios. The curves are given for wings having straight taper and distorted elliptical plan forms. The characteristics of wings of other shapes may be determined by interpolation.
    Type: NACA-TN-483
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  • 43
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    The Effect of Spray Strips on a Model of the P3M-1 Flying Boat Hull (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results of a series of tests made in the N.A.C.A. tank on a one-sixth full-size model of the hull and side floats of the Navy P3M-1 flying boat for the purpose of finding a method of reducing the amount of spray thrown into the propellers of this craft when taking off and landing. The model was tested without spray strips and with five different spray-strip arrangements. The best arrangement was an improvement over the bare hull with no spray strips, but the improvement was not sufficient to be satisfactory with the propellers in the designed position.
    Type: NACA-TN-482
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  • 44
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    The Reduction in Drag of a Forward-sloping Windshield (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper gives results of a short investigation of the drag of a forward-sloping closed-cabin windshield. The drag of the windshield in both the original and a final modified form was determined from tests in the variable-density wind tunnel. The final form of the windshield was arrived at by modifying the original as the result of flow observations in the N.A.C.A. smoke tunnel. The investigation studied the utility of the N.A.C.A. smoke tunnel as applied to reducing the drag of objects for which the full dynamic scale could not be approached in the smoke tunnel, but designers should find the results of the flow observations and drag measurements of value. They show that most of the large drag added by the original windshield is eliminated by the modification of the windshield to the final form.
    Type: NACA-TN-481
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  • 45
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    The Drag of Streamline Wires (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preliminary results are given of drag tests of streamline wires. Full-size wires were tested over a wide range of speeds in the N.A.C.A. high speed tunnel. The results are thus directly applicable to full-scale problems and include any compressibility effects encountered at the higher speeds. The results show how protuberances may be employed on conventional streamline wires to reduce the drag, and also show how the conventional wires compare with others having sections more like strut or symmetrical airfoil sections. Because the new wire sections developed are markedly superior aerodynamically to conventional wires, it is recommended that some of them be tested in service in order to investigate their relative susceptibility to vibration and to fatigue failure.
    Type: NACA-TN-480
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  • 46
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    Engine performance with a hydrogenated safety fuel (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the engine performance obtained with a hydrogenated safety fuel developed to eliminate fire hazard. The tests were made on a single-cylinder universal test engine at compression ratios of 5.0, 5.5, and 6.0. Most of the tests were made with a fuel-injection system, although one set of runs was made with a carburetor when using gasoline to establish comparative performance. The tests show that the b.m.e.p. obtained with safety fuel when using a fuel-injection system is slightly higher than that obtained with gasoline when using a carburetor, although the fuel consumption with safety fuel is higher. When the fuel-injection system is used with each fuel and with normal engine temperatures the b.m.e.p. with safety fuel is from 2 to 4 percent lower than with gasoline and the fuel consumption about 25 to 30 percent higher. However, a few tests at an engine coolant temperature of 250 F have shown a specific fuel consumption approximating that obtained with gasoline with only a slight reduction in power. The idling of the test engine was satisfactory with the safety fuel. Starting was difficult with a cold engine but could be readily accomplished when the jacket water was hot. It is believed that the use of the safety fuel would practically eliminate crash fires.
    Type: NACA-TN-466
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  • 47
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    Some Characteristics of Sprays Obtained from Pintle-type Injection Nozzles (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests made with the pintle-type injection nozzles, one having a pintle angle of 8 degrees, the other a pintle angle of 30 degrees. The fuel was injected into a glass-windowed pressure chamber and the spray photographed by means of the N.A.C.A. spray photography apparatus. Curves are presented that give the penetration of the spray tips when fuel oil is injected by pressures of 1,500 to 4,000 pounds per square inch into air at room temperature and densities of 11 to 18 atmospheres. High-speed spark photographs show the appearance of the sprays in air at a density of 18 atmospheres. The results indicate that the pintle angles have little effect on the size of the spray cone angle, which is about the same as that of sprays from plain round hole orifices. The penetration of the spray from the nozzle with an 8 degree pintle is slightly higher than that of the spray from the nozzle with a 30 degree pintle. The penetration of the sprays from the pintle nozzles, for comparable conditions of injection pressure and air density, is about the same as that of sprays from round-hole orifices. Increase in air density decreases the penetration in about the same ratio with all the injection pressures.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-465
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  • 48
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    A complete tank test of a model of a flying-boat hull-N.A.C.A. Model No.11 (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of comparison and application. A practical problem using the characteristics of model no.11 is presented to show the method of calculating the take-off time and run of a seaplane from these data.
    Type: NACA-TN-464
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  • 49
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    Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests were made of a model wing having an aspect ratio of 3 and a tapered plan form with a straight trailing edge. The model had the Clark Y airfoil section throughout it's entire span and had no washout, depending on a trailing-edge flap for longitudinal balance and control. The flap had a constant chord and was divided into four equal portions along the span. The tests were made with the entire flap deflected to obtain longitudinal control and balance, and also with the inner portions deflected alone, and with the outer portions deflected alone. It was found that the simple wing with no washout or change of basic section along the span has aerodynamic characteristics well suited for use on tailless airplanes. A higher lift coefficient was obtained with the full-span flap deflected as a unit to give longitudinal balance than was obtained with either the inner or the outer portions of the flap deflected.
    Type: NACA-TN-463
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  • 50
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    Formulas for the Stress Analysis of Circular Rings in a Monocoque Fuselage (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The formulas given in this report provide a simplified method for the stress-analysis of fuselage bulkheads that are approximately circular rings of uniform cross section. Complicated load systems acting on a ring can usually be resolved into simplified load systems; and formulas for moment, axial force, and shear for such simplified load systems are given in this report. Illustrative examples showing the use of this method in practical stress-analysis work are also included.
    Type: NACA-TN-462
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  • 51
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    Strength Tests of Thin-walled Duralumin Cylinders in Pure Bending (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the third of a series presenting the results of strengths tests on thin-walled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from pure bending tests on 58 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that the stress on the extreme fiber at failure as calculated by the ordinary theory of bending is from 30 to 80 percent greater than the compressive stress at failure for thin-walled cylinders in compression. The tests also show that length/radius ratio has no consistent effect upon the bending strength and that the size of the wrinkles that form on the compression half of a cylinder in bending is approximately equal to the size of the wrinkles that form in the complete circumference of a cylinder of the same dimensions in compression.
    Type: NACA-TN-479
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  • 52
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    The Effect of Rivet Heads on the Characteristics of a 6 by 36 Foot Clark Y Metal Airfoil (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the N.A.C.A. full-scale wind tunnel to determine the effects of exposed rivet heads on the aerodynamic characteristics of a metal-covered 6 by 36 foot Clasky airfoil. Lead punching simulating 1/8inch rivet heads were attached in full-span rows at a pitch of 1 inch at various chord positions. Tests were made at velocities varying from 40 to 120 miles per hour to investigate the scale effect. Rivets at the 5 percent chord position the upper surface of the airfoil produced the greatest increase in drag for a single row. Nine rows of rivets on both surfaces, simulating rivet spacing of multispan construction, increased the drag coefficients by a constant amount at velocities between 100 and 120 miles per hour. Accordingly, if rivets spaced the same as those on the test airfoil were used on a Clark Y wing of 300 square feet area and operated at 200 miles per hour, the drag would be increased over that for the smooth wing by 55 pounds and the power required would be increased by 29 horsepower.
    Type: NACA-TN-461
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  • 53
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    The Effects of Slots and Flaps on Lateral Control of a Low-wing Monoplane as Determined in Flight (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of flight tests made to determine the effect of slots and flaps on the lateral control of a low-wing monoplane. Maximum angular accelerations in roll and yaw produced by sudden application of the ailerons and maximum accelerations in yaw produced by sudden application of the rudder during gliding flight were recorded for the following wing arrangements: (a) no auxiliary device; (b) full-span slots; (c) plain flaps; (d) flaps and full-span slots; (e) wing-tip slots. Rolling- and yawing-moment coefficients were derived from the accelerations. The full span slots and the flaps each had about the same influence on the aileron rolling moments. At values of the lift coefficient obtainable with the plain wing, the effect of these devices was negligible. At the higher lift coefficients obtainable with these devices, the rolling-moment coefficients increased slightly but, despite this increase, the aileron effectiveness progressively decreased with increasing lift coefficient, owing to the corresponding reduction in air speed. In the range covered by the tests, the effectiveness of the controls was appreciably reduced by the wing-tip slots. The adverse yawing moment of the ailerons experienced at the large lift coefficients obtained with the flaps was appreciably less than at similar lift coefficients obtained with either full-span or wing-tip slots. The yawing moments produced by the rudder were only slightly affected by the use of the auxiliary devices. The airplane was found to be laterally unstable with all combinations tested. Because of the angular velocities acquired in the time taken to deflect the ailerons the rolling moments recorded in flight were only about two thirds the values that would have been obtained with the wing restrained as in wind-tunnel tests.
    Type: NACA-TN-478
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  • 54
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    The effect on engine performance of change in jacket-water outlet temperature (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests made on a Curtiss D-12 engine in the Altitude Laboratory at the Bureau of Standards show the following effects on engine performance of change in jacket-water outlet temperature: 1) Friction at all altitudes is a linear function of the jacket-water temperature, decreasing with increasing temperature. 2) The brake horsepower below an altitude of about 9,000 feet decreases, and at higher altitudes increases, with jacket-water temperature. 3) The brake specific fuel consumption tends to decrease, at all altitudes, with increasing jacket-water temperature. 4) The percentage change in brake power output is roughly equal to the algebraic sum of the percentage change in volumetric efficiency and mechanical efficiency.
    Type: NACA-TN-476
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  • 55
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    Full-scale Wind-tunnel Research on Tail Buffeting and Wing-fuselage Interference of a Low-wing Monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some preliminary results of full scale wind tunnel testing to determine the best means of reducing the tail buffeting and wing-fuselage interference of a low-wing monoplane are given. Data indicating the effects of an engine cowling, fillets, auxiliary airfoils of short span, reflexes trailing edge, propeller slipstream, and various combinations of these features are included. The best all-round results were obtained by the use of fillets together with the National Advisory Committee for Aeronautics (NACA) cowling. This combination reduced the tail buffeting oscillations to one-fourth of their original amplitudes, increased the maximum lift 11 percent, decreased the minimum drag 9 percent, and increased the maximum ratio of lift to drag 19 percent.
    Type: NACA-TN-460
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  • 56
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    Wind tunnel research comparing lateral control devices, particularly at high angles of attack XI : various floating tip ailerons on both rectangular and tapered wings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Discussed here are a series of systematic tests being conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present tests were made with six different forms of floating tip ailerons of symmetrical section. The tests showed the effect of the various ailerons on the general performance characteristics of the wing, and on the lateral controllability and stability characteristics. In addition, the hinge moments were measured for the most interesting cases. The results are compared with those for a rectangular wing with ordinary ailerons and also with those for a rectangular wing having full-chord floating tip ailerons. Practically all the floating tip ailerons gave satisfactory rolling moments at all angles of attack and at the same time gave no adverse yawing moments of appreciable magnitude. The general performance characteristics with the floating tip ailerons, however, were relatively poor, especially the rate of climb. None of the floating tip ailerons entirely eliminated the auto rotational moments at angles of attack above the stall, but all of them gave lower moments than a plain wing. Some of the floating ailerons fluttered if given sufficiently large deflection, but this could have been eliminated by moving the hinge axis of the ailerons forward. Considering all points including hinge moments, the floating tip ailerons on the wing with 5:1 taper are probably the best of those which were tested.
    Type: NACA-TN-458
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  • 57
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    The Aerodynamic Characteristics of Airfoils as Affected by Surface Roughness (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect on airfoil characteristics of surface roughness of varying degrees and types at different locations on an airfoil was investigated at high values of the Reynolds number in a variable density wind tunnel. Tests were made on a number of National Advisory Committee for Aeronautics (NACA) 0012 airfoil models on which the nature of the surface was varied from a rough to a very smooth finish. The effect on the airfoil characteristics of varying the location of a rough area in the region of the leading edge was also investigated. Airfoils with surfaces simulating lap joints were also tested. Measurable adverse effects were found to be caused by small irregularities in airfoil surfaces which might ordinarily be overlooked. The flow is sensitive to small irregularities of approximately 0.0002c in depth near the leading edge. The tests made on the surfaces simulating lap joints indicated that such surfaces cause small adverse effects. Additional data from earlier tests of another symmetrical airfoil are also included to indicate the variation of the maximum lift coefficient with the Reynolds number for an airfoil with a polished surface and with a very rough one.
    Type: NACA-TN-457
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  • 58
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    The Effect of Split Trailing-edge Wing Flaps on the Aerodynamic Characteristics of a Parasol Monoplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of tests conducted in the N.A.C.A. full-scale wind tunnel on a Fairchild F-22 airplane equipped with a special wing having split trailing-edge flaps. The flaps extended over the outer 90 percent of the wing span, and were of the fixed-hinge type having a width equal to 20 percent of the wing chord. The results show that with a flap setting of 59 degrees the maximum lift of the wing was increased 42 percent, and that the flaps increased the range of available gliding angles from 2.7 degrees to 7.0 degrees. Deflection of the split flaps did not increase the stalling angle or seriously affect the longitudinal balance of the airplane. With flaps down the landing speed of the airplane is decreased, but the calculated climb and level-flight performance is inferior to that with the normal wing. Calculations indicate that the take-off distance required to clear an obstacle 100 feet high is not affected by flap settings from 0 degrees to 20 degrees but is greatly increased by larger flap angles.
    Type: NACA-TN-475
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  • 59
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    The Aerodynamic Effect of a Retractable Landing Gear (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels were extended reduced the drag only 2 percent at a lift coefficient of 1.0, which was assumed for the take-off condition. Therefore, the wheel openings in the bottom side of the wing have a negligible effect upon the take-off of the airplane. Retracting the landing gear reduced the minimum drag of the complete airplane 50 percent.
    Type: NACA-TN-456
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  • 60
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    Effect of stabilizer location upon pitching and yawing moments in spins as shown by tests with the spinning balance (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made with the spinning balance in a 5-foot wind tunnel to study the effect of stabilizer location upon the pitching and yawing moments given by the tail surfaces in spinning attitudes. The tests revealed that the horizontal surfaces, when in a normal location, seriously reduced the effectiveness of the fin and rudder, particularly at angles of attack of 50 degrees or more. The tests also revealed that a more forward or more rearward location gave no consistent or decided improvement; that a lower location greatly increased the shielding so that the yawing moment from the combination was in general less than that given by the bare fuselage; and that a higher location decreased the shielding and gave a favorable interference effect, particularly at the high angles of attack. Additional results regarding the stabilizer and the elevator are given.
    Type: NACA-TN-474
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  • 61
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    Comparison of Three Methods for Calculating the Compressive Strength of Flat and Slightly Curved Sheet and Stiffener Combinations (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a comparison of the accuracy of the three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressed-skin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffener and an effective width as a column gave the best agreement with the results of the tests. An investigation of the effect of small curvature resulted in the conclusion that the compressive strength of the curved panels is, for all practical purposes, equal to the strength of flat panels except for thick sheet where non-uniform curvature throughout the length may cause the strength of the curved panel to be 10 to 15 percent less than that of a corresponding flat panel.
    Type: NACA-TN-455
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  • 62
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    Tank Tests of Two Floats for High-speed Seaplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: At the request of the Bureau of Aeronautics, Navy Department, a study of the design of floats especially suitable for use on high-speed seaplanes was undertaken in the N.A.C.A. tank. This note give the results obtained in tests of one-quarter full-size models of two floats for high-speed seaplanes. One was a float similar to that used on the Macchi high-speed seaplane which competed in the 1926 Schneider Trophy races, and the other a float designed at the N.A.C.A. tank in an attempt to improve on the water performance of the Macchi float. The model of the latter showed considerably better water performance than the model of the Macchi float.
    Type: NACA-TN-473
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  • 63
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    Experiments with a Counter-propeller (1933)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: This note describes tests made at Stanford University on a four-blade fixed counter-propeller in combination with a two-blade rotating propeller. It is shown that the efficiency of the normal form, well-designed air propeller can be increased about two percent over the full working range by the addition of fixed counter-propeller blades.
    Type: NACA-TN-453
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  • 64
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    The effect of partial-span split flaps on the aerodynamic characteristics of a Clark Y wing (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a model Clark Y wing with a 20 percent chord split flap deflected 60 degrees downward. The tests were made to determine the effect of partial-span split flaps, located at various positions along the wing span on the aerodynamic characteristics of the wing-and-flap combination. The different lengths and locations of the flaps were obtained by cutting off portions of a full-span flap, first from the tips and then from the center. The results are given in the form of curves of lift, drag, and center of pressure. They show that with partial-span split flaps both the lift and drag are less than with full-span flaps; that the lift for a given length of flap is somewhat greater when the partial span is located at the center of the wing than when it is located at the tip portion, and that the drag for a given length of flap is the same regardless of the location over the flap with respect to the wing span.
    Type: NACA-TN-472
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  • 65
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    The N.A.C.A. Combustion Chamber Gas-sampling Valve and Some Preliminary Test Results (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A gas sampling valve of the inertia-operated type was designed for procuring samples of the gases in the combustion chamber of internal combustion engines at identical points in successive cycles so that the analysis of the gas samples thus procured may aid in the study of the process of combustion. The operation of the valve is described. The valve was used to investigate the CO2 content of gases taken from the quiescent combustion chamber of a high speed compression-ignition engine when operating with two different multiple-orifice fuel injection nozzles. An analysis of the gas samples thus obtained shows that the state of quiescence in the combustion chamber is maintained during the combustion of the fuel.
    Type: NACA-TN-454
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  • 66
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    A Complete Tank Test of a Model of Flying-boat Hull - N.A.C.A. Model 16 (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A model of a 2-step flying-boat hull, of the type generally used in England, was tested according to the complete method described in the N.A.C.A. Technical Note No. 464. The lines of this model were taken from offsets given by Mr. William Munro in Flight, May 29, 1931. The data cover the range of loads, speeds, and trim angles that may be of use in applying the hull form to the design of any seaplane. The results are reduced to nondimensional form to aid application to design problems and facilitate comparison with the performance of other hulls. The water characteristics of Model 16 are compared with those of Model 11-A, which is representative of current American practice. The results show that when the two forms are applied to a given seaplane design under optimum conditions for each, the performance of Model 16 will be somewhat inferior to that of Model 11-A.
    Type: NACA-TN-471
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  • 67
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    A Complete Tank Test of a Model of a Flying-boat Hull - N.A.C.A. Model No.11-A (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Model No. 11-A was designed as an improvement over N.A.C.A. Model No. 11, a complete test of which is described in N.A.C.A. Technical Note No. 464. In contrast with the longitudinal upward curvature in the planing bottom forward of the main step on Model 11-A was made as flat as practicable. Otherwise, the two models have very nearly the same form. The results of towing tests made on Model 11-A in the N.A.C.A. tank over a wide range of speed, load on the water, and trim angle are presented, both as original test data and as non dimensional coefficients. A comparison is made with similar results from the test of Model No. 11. The practical significance of the improvement obtained is demonstrated by applying the data from the new form to the illustrative design problem use in the note on Model NO. 11.
    Type: NACA-TN-470
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  • 68
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    A Summary of Design Formulas for Beams Having Thin Webs in Diagonal Tension (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents an explanation of the fundamental principles and a summary of the essential formulas for the design of diagonal-tension field beams, i.e. beams with very thin webs, as developed by Professor Wagner of Germany.
    Type: NACA-TN-469
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  • 69
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    Wind tunnel research comparing lateral control devices, particularly at high angles of attack X : various control devices on a wing with a fixed auxiliary airfoil (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are given of a series of systemic tests comparing lateral control devices with particular reference to their effectiveness at high angles of attack. These tests were made with two sizes of ordinary ailerons and different sizes of spoilers on a Clark Y wing model having a narrow auxiliary airfoil fixed ahead and above the leading edge, the chords of the main and auxiliary airfoils being parallel. In addition, the auxiliary airfoil itself was given angular deflection. The purpose was to provide rolling moments for lateral control. The tests were made in a 7 by 10 foot wind tunnel. They included both force and rotation tests to show the effect of the devices on the lift and drag characteristics of the wing and on the lateral stability characteristics, as well as lateral control. They showed that none of the aileron arrangements tried would give rolling control of an assumed satisfactory value at all angles of attack up to the stall. However, they would give satisfactory values, but at the expense of abnormally high deflections and very heavy hinge moments. The most effective combination of ailerons and spoilers gave satisfactory values of rolling moment at angles of attack below the stall, and the values did not fall off as rapidly above the stall as with ailerons alone. With an arrangement of this type having the proper relative proportions and linkage, it should be possible to obtain reasonably satisfactory yawing moments and control forces. Deflecting one-half of the auxiliary airfoil downward for the purpose of control gave strong favorable yawing moments at all angles of attack, but gave very small rolling moments at the low angles of attack.
    Type: NACA-TN-451
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  • 70
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    A study of factors affecting the steady spin of an airplane (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data from wind-tunnel tests on a model of the NY-1 airplane were used in a study of the effect on the steady spin of a number of factors considered to be important. The factors were of two classes, mass distribution effects and aerodynamic effects. The study indicated that mass extended along the longitudinal axis has no detrimental effect or is even slightly beneficial, mass extended along the lateral axis is detrimental if the airplane spins with the inner wing tip far down, and mass extended along the normal axis, if of considerable magnitude, has a strong favorable effect. The aerodynamic effects considered in terms of rolling, pitching, and yawing moments added to those for a conventional airplane showed that added stable rolling moment could contribute favorable effect on the spin only in decreasing the amount of inward sideslip required for equilibrium. Negative pitching moment of moderate magnitude has unfavorable effect on a high-angle-of-attack spin, and stable yawing moment has pronounced beneficial effect on the spin. Experimental data from various sources were available to verify nearly all the deductions resulting from the study of the curves. When these results were considered for the purpose of deciding upon the best means to be developed for controlling the spin, the yawing-moment equilibrium was found to offer the most promising field for research. The wing-cellule yawing moment, of which the shape of the chord-force curve is an approximate measure, should be made as small as possible in the unstable sense and the damping yawing moment of the tail should be made as large as possible. The most serious unfavorable effect on the damping yawing moment of the tail is the blanketing of the vertical surfaces by the other parts of the tail.
    Type: NACA-TN-468
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  • 71
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    Mercerization of Cotton for Strength with Special Reference to Aircraft Cloth (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The object of the present investigation was to determine the conditions for mercerizing cotton yarn to obtain the maximum strength for a given weight. Apparatus for controlling the variables was built and yarns were mercerized with it under systematically varied conditions of tension, time, temperature, and concentration of caustic soda. The strongest conclusion to be drawn from this work is that the strongest mercerized yarn of a given count from a given quality of cotton is obtained under the following conditions: 1. use of low-twist yarn obtained with twist multipliers from 2.2 to 3; 2. thorough pretreatment of the yarn to remove all extraneous materials; 3. mercerization at a temperature of 0 C or lower; 4. use of sufficient tension during mercerization to prevent the yarn from contracting more than 3 percent. 5. Use of caustic solution having a concentration of 10 percent or higher; 6. the time of mercerization to be 5 minutes. The resulting yarn should be 40 to 100 percent stronger than the original yarn of the same weight.
    Type: NACA-TN-450
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  • 72
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    Wind-tunnel research comparing lateral control devices, particularly at high angles of attack IX : tapered wings with ordinary ailerons (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made with ordinary flap-type ailerons on two wings with different amounts of taper, one medium and the other extreme. On each wing both medium sized tapered ailerons and short wide tapered ailerons were tested.
    Type: NACA-TN-449
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  • 73
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    Effect of aileron displacement on wing characteristics (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of aileron displacement on wing characteristics has been investigated for the Clark Y and the U.S.A. 27 wing sections equipped with rectangular ailerons. The airfoils, rectangular in plan, and having a 10 inch chord and 60 inch span, were mounted on a model fuselage.
    Type: NACA-TN-448
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  • 74
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    The Effect on Lift, Drag, and Spinning Characteristics of Sharp Leading Edges on Airplane Wings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation with special reference to auto rotation and spinning was conducted in two wind tunnels and in flight to find the aerodynamic effects of adding a sharp leading edge to a wing sector.
    Type: NACA-TN-447
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  • 75
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    Wind tunnel research comparing lateral control devices, particularly at high angles of attack VIII : straight and skewed ailerons on wings with rounded tips (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, as well as on the lateral control and stability characteristics. The hinge moments were not measured but the approximate values are given in the first report of the series.
    Type: NACA-TN-445
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  • 76
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    Working charts for the stress analysis of elliptic rings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents charts which reduce the stress analysis of circular and elliptic rings of uniform cross section subjected to balanced systems of concentrated loads from a statically indeterminate problem to a statically determinate one. To demonstrate the use of the charts in the stress analysis of elliptic rings, an illustrative problem is included.
    Type: NACA-TN-444
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  • 77
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    Wind tunnel research concerning lateral control devices, particularly at high angles of attack VII : Handley Page tip and full-span slots with ailerons and spoilers (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made with ordinary ailerons and different sizes of spoilers on rectangular Clark Y wing models with Handley Page tip and full span slots. The tests showed the effect of the control devices on the general performance of the wings as well as on the lateral control and lateral stability characteristics.
    Type: NACA-TN-443
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  • 78
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    Jet Propulsion with Special Reference to Thrust Augmenters (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the possibility of using thrust augmented jets as prime movers was carried out. The augmentation was to be effected by allowing the jet to mix with the surrounding air in the presence of bodies which deflect the air set in motion by the jet.
    Type: NACA-TN-442
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  • 79
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    Rolling, yawing, and hinge moments produced by rectangular ailerons (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Ailerons described in references 1, 2, and 3, are summarized in the form of empirical equations which relate the aileron dimensions and displacements to the rolling, yawing, and hinge moments for pitch angles of 0 and 12 degrees, corresponding to angles of attack of the wings of 4 and 16 degrees, respectively.
    Type: NACA-TN-441
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  • 80
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    Knowledge Gained from Practical Experience in the Designing of Aircraft Engines (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report examines a few important points of engine design such as: in-line water cooled engines, air-cooled in-line engines, and air-cooled radial engines. Subassemblies are also discussed like cylinder types, blower driving gears, pistons, valves, bearings, and crankshafts.
    Type: NACA-TM-706
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  • 81
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    Flight-test data on the static fore-and-aft stability of various German airplanes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The static longitudinal stability of an airplane with locked elevator is usually determined by analysis and model tests. The present report proposes to supply the results of such measurements. The method consisted of recording the dynamic pressure versus elevator displacement at different center-of-gravity positions in unaccelerated flight.
    Type: NACA-TM-708
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  • 82
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    Scale Effect of Model in Seaplane-float Investigations (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For the purpose of solving all the problems involved, an investigation was made with flat, rectangular planing surfaces. The investigation of a flat, rectangular planing surface, which can be considered as the portion of a flat float bottom lying in front of the step, has the advantage that the frictional resistance can be determined directly from the test results. Normal and tangential forces act on the lower side of the planing surface towed through still water, while the upper side and the lateral edges are under constant atmospheric pressure.
    Type: NACA-TM-704
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  • 83
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    The Schneider Trophy Contest (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a history of the Schneider trophy race with special emphasis of England's win in the 1931 race. Lift and drag are reported on and discussed extensively.
    Type: NACA-TM-712
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  • 84
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    A simple method for increasing the lift of airplane wings by means of flaps (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic considerations led us, not long ago, to investigate a device which seemed to promise a contribution to the problem of reducing the landing speed of an airplane. We have subsequently learned that similar devices had already been proposed and investigated by others, but it seems advisable, nevertheless, to report our results. The problem is to create, in landing, a region of turbulence on the lower side of the wing near the trailing edge by some obstacle to the air flow. The devices tested by us consisted of flaps of varying chord and position, the chord s being equal to the distance of the pivot from the trailing edge.
    Type: NACA-TM-714 , Wissenschaftliche Gesellschaft fur Luftfahrt (21st : 1932 : Berlin)
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  • 85
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    Increasing the volumetric efficiency of Diesel engines by intake pipes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Development of a method for calculating the volumetric efficiency of piston engines with intake pipes. Application of this method to the scavenging pumps of two-stroke-cycle engines with crankcase scavenging and to four-stroke-cycle engines. The utility of the method is demonstrated by volumetric-efficiency tests of the two-stroke-cycle engines with crankcase scavenging. Its practical application to the calculation of intake pipes is illustrated by example.
    Type: NACA-TM-700
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  • 86
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    Determination of Inherent Stresses by Measuring Deformations of Drilled Holes (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Various methods have been proposed for determining the inherent stresses in structural components by disturbing their stress equilibrium through a mechanical device and measuring the resulting deformations. The methods used have disadvantages because they can be used only with specially shaped pieces (those with round or rectangular cross sections), that every form of test piece requires another kind of injury and hence of calculation, and the tested parts are rendered useless. The new test method, which seeks to eliminate these disadvantages, is likewise based on a disturbance of the equilibrium of forces, and indeed by drilling a hole which, however, is so small that the part can be used again. This method serves, among other things, for determining the inherent stresses in castings, welded parts, rolled structural shapes and finished structures.
    Type: NACA-TM-702
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  • 87
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    The critical shear load of rectangular plates (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives formulas for analyzing the critical shear load of a simply supported square, isotropic (simple flat plate), or orthogonal anisotropic plate (a plate in which the rigidity in two directions perpendicular to each other is different, i.e. plywood or corrugated sheet), these formulas, although arrived at by approximation method, seem to agree fairly well with experimental results.
    Type: NACA-TM-705
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  • 88
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    Pressure Rise, Gas Vibrations and Combustion Noises During the Explosion of Fuels (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the use of piezo-quartz indicators for high-speed automobile engines, the interpretation of pressure-time diagrams made by an oscillograph offers certain difficulties. On the one hand, the scale of the pressure amplitudes is not always the same under all conditions, while, on the other hand, the atmospheric zero line may be shifted from its correct position in the oscillogram. These facts make necessary to verify the readings of the quartz indicators by direct calibration before and after each series of tests and, on the basis of the results, to determine the scale for the oscillograms.
    Type: NACA-TM-711
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  • 89
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    Pressure and frictional resistance of a cylinder at Reynolds numbers 5,000 to 40,000 (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a series of free-jet measurements to determine the pure frictional resistance of a cylinder from the difference between total resistance and pressure at Reynolds Numbers 5,000 to 40,700. The skin friction is 5 percent of the total resistance at Re = 5,000, and had dropped to 2 percent at Re = 40,000, which supports Thom's theory.
    Type: NACA-TM-715
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  • 90
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    Development of the rules governing the strength of airplanes. Part II : loading conditions in Germany (continued), England and the United States (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Load factors and loading conditions are presented for Germany, England, and the United States. Results of tests are presented and loading conditions are presented under various stress categories like freight, commercial, aerobatics, and training.
    Type: NACA-TM-717
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  • 91
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    Recent Results of Turbulence Research (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The first sections of this report deal with two prominent questions, namely the origin of turbulence and the characteristics of turbulent currents. In the third section conclusions are drawn for the flow along a rough wall, whereby an important relation for the velocity distribution is revealed. The principles are also applied to straight rough and smooth tubes.
    Type: NACA-TM-720
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  • 92
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    Dimensions of twin seaplane floats (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the characteristics of floats submitted to the test committee and the tests performed on them.
    Type: NACA-TM-719
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  • 93
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    The 1933 Contest for the Deutsch De La Meurthe Trophy (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-724
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  • 94
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    The effect of humidity on engine power at altitude (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From tests made in the altitude chamber of the Bureau of Standards, it was found that the effect of humidity on engine power is the same at altitudes up to 25,000 feet as at sea level. Earlier tests on automotive engines, made under sea-level conditions, showed that water vapor acts as an inert diluent, reducing engine power in proportion to the amount of vapor present. By combining the effects of atmospheric pressure, temperature, and humidity, it is shown that the indicated power obtainable from an engine is proportional to its mass rate of consumption of oxygen. This has led the National Advisory Committee for Aeronautics to adopt a standard basis for the correction of engine performance, in which the effect of humidity is included.
    Type: NACA-TR-426
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  • 95
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    Measurement of the Differential and Total Thrust and Torque of Six Full-Scale Adjustable-Pitch Propellers (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Force measurements giving total thrust and torque, and propeller slip stream surveys giving differential thrust and torque were simultaneously made on each of six full-scale propellers in the 20-foot propeller-research tunnel of the National Advisory Committee for Aeronautics. They were adjustable-pitch metal propellers 9.5 feet in diameter; three had modified Clark Y blade sections and three had modified RAF-6 blade sections. This report gives the differential thrust and torque and the variation caused by changing the propeller tip speed and the pitch setting. The total thrust and torque obtained from integration of the thrust and torque distribution curves are compared with those obtained by direct force measurements.
    Type: NACA-TR-421
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  • 96
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    Experiments on the Distribution of Fuel in Fuel Sprays (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The distribution of fuel in sprays for compression-ignition engines was investigated by taking high-speed spark photographs of fuel sprays reproduced under a wide variety of conditions, and also by injecting them against pieces of plasticine. A photographic study was made of sprays injected into evacuated chambers, into the atmosphere, into compressed air, and into transparent liquids. Pairs of identical sprays were injected counter to each other and their behavior analyzed. Small high velocity air jets were directed normally to the axes of fuel sprays, with the result that the envelope of spray which usually obscures the core was blown aside, leaving the core exposed on one side. The results showed that the distribution of the fuel within the sprays was very uneven.
    Type: NACA-TR-438
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  • 97
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    Force Measurements on a 1/40-scale Model of the U. S. Airship "Akron." (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes a series of tests made on a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4) for the purpose of determining the drag, lift, and pitching moments of the bare hull and of the hull equipped with two different sets of fins. Measurements were also made of the elevator forces and hinge moments.
    Type: NACA-TR-432
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  • 98
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    Wind-tunnel research comparing lateral control devices, particularly at high angles of attack IV : floating tip ailerons on rectangular wings (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the fourth of a series on systematic tests conducted which compares lateral control devices with particular reference to their effectiveness at high angles of attack. The present report covers tests with floating tip ailerons on rectangular Clark y wings. Ailerons of two profiles were tested - symmetrical and Clark y, both with adjustable trailing-edge flaps. Each form was tested at three hinge-axis locations, both with and without vertical end plates between the ailerons and the wing proper. The results from these tests are compared with the results from tests on a wing of the same over-all size equipped with average-sized ordinary ailerons.
    Type: NACA-TR-424
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  • 99
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    Aircraft Speed Instruments (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a concise survey of the measurement of air speed and ground speed on board aircraft. Special attention is paid to the pitot-static air-speed meter which is the standard in the United States for airplanes. Air-speed meters of the rotating vane type are also discussed in considerable detail on account of their value as flight test instruments and as service instruments for airships. Methods of ground-speed measurement are treated briefly, with reference to the more important instruments. A bibliography on air-speed measurement concludes the report.
    Type: NACA-TR-420
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  • 100
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    Preliminary Investigation of Modifications to Conventional Airplanes to Give Nonstalling and Short-Landing Characteristics (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes flight and landing tests made on a group of conventional airplanes. The upward deflection of the elevators was limited to the point where the airplanes could not be made to spin without the aid of power. With the elevator travel thus limited, the airplane in every case had good lateral stability and good aileron effectiveness up to the highest angles of attack which could be obtained in a glide, although this was not true in any case without the limited control. All ordinary flight maneuvers could be performed with the elevator displacement limited, but usually there was not sufficient control to get the tail down for a normal 3-point landing.
    Type: NACA-TR-418
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