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  • 1940  (196)
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  • 1
    facet.materialart.
    Unbekannt
    [Neue Nr. 5160] Bad Warmbrunn [Cieplice Śląskie-Zdrój] / Geologische Karte (1940)
    Berliner Lithogr. Inst., Berlin
    In:  SUB Göttingen | KART B 140:5160[1940];KART H 140:Bad Warmbrunn
    Details
    Publikationsdatum: 2024-02-21
    Beschreibung: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften der festen Erde), erstellt durch das GDZ (Göttinger Digitalisierungszentrum, SUB Göttingen), Karte aus dem Bestand der SUB Göttingen. GeoTIFF erstellt durch FID GEO, SUB Göttingen.
    Beschreibung: map
    Beschreibung: DFG, SUB Göttingen
    Schlagwort(e): ddc:912 ; ddc:554.3 ; Geologische Karte ; Warmbrunn ; Cieplice Śląskie-Zdrój ; GeoTIFF
    Sprache: Deutsch
    Materialart: doc-type:carthographicMaterial
    Standort Signatur Erwartet Verfügbarkeit
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    CITATION GEO-LEO
  • 2
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    Form and nature of seismic waves and the structure of seismograms (1940)
    In:  Geophysics, Luxembourg, National Academy of Sciences of the USA, vol. 5, no. 1-2, pp. 348, pp. B05311, (ISSN: 1340-4202)
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 3
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    The form and nature of seismic waves and the structure of seismograms (1940)
    In:  Geophysics, Luxembourg, National Academy of Sciences of the USA, vol. 6, no. 1-2, pp. 254, pp. B05311, (ISSN: 1340-4202)
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 4
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    Seismicity of the earth (1940)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 51, no. 6, pp. 1958, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1940
    Schlagwort(e): Seismicity
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 5
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    Unbekannt
    Handbuch der Geophysik, Volume 10: Allgemeines (only 1st part) (1940)
    Bornträger
    In:  Berlin, 4 + 117 S., Bornträger, vol. 7, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publikationsdatum: 1940
    Schlagwort(e): Handbook of geophysics
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 6
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    Unbekannt
    Seismological Tables (1940)
    British Association for the Advancement of Science, Gray Milne Trust
    In:  London, 50 pp., 4th print., 1970, British Association for the Advancement of Science, Gray Milne Trust, vol. 46, no. XVI:, pp. 1-14, (ISBN: 0-387-30752-4)
    Details
    Publikationsdatum: 1940
    Schlagwort(e): Earth model, also for more shallow analyses ! ; Travel time ; Seismology ; Handbook of geophysics
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 7
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    Eingehen von Kiefernspannerraupen durch Frost? (1940)
    In:  Ztschr. Forst-, Jagdwesen 72: 246-255
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 8
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    Winterschäden 1939/40 in Hinterpommern. Unter besonderer Berücksichtigung meiner Erfahrungen mit Nadelhölzern und immergrünen Gehölzen (1940)
    In:  Mitt. dtsch. dendrol. Ges., Nr. 53 (Jahrb.): 293-299
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 9
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    Anzucht und Anbau der Pappel. (1940)
    In:  Dtsch. Forstwirt 22:153-157
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 10
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    Der Einfluß er Bodenbearbeitung auf das Wachstum von Laubholz auf armen Sandböden (1940)
    In:  Forstarchiv 16: 96-105
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 11
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    Resistenz einiger Durchforstungsarten gegen Schneebrüche (1940)
    In:  Sborník Ceskosl. Akad. Zemed., Praha, 15: 350-355
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 12
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    Frostschäden an Eichen. Aus der Geschichte des Forstamtes Grimnitz/Uckermark. (1940)
    In:  Ztschr. Forst- u. Jagdwes. 72: 3-35
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 13
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    The Physikal effects of drought on shade trees (1940)
    In:  West. Shade Tree Conf. Proc 7: 21-30
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 14
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    Ernährungsphysiologische Untersuchungen an Nonnenraupen (Lymantria monacha L.). I. u. II. Teil. (1940)
    In:  Ztschr. angew. Ent. 27: 157-207 u. 408-449
    Details
    Publikationsdatum: 1940
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 15
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    Malaria und Malariaübertragung in Ostfriesland (1940)
    In:  Archiv für Schiffs- und Tropenhygiene 44, 1-73
    Details
    Publikationsdatum: 1940
    Schlagwort(e): Norddeutschland ; Umweltmedizin ; Infektionskrankheiten
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 16
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    Inwieweit berücksichtigt der Landwirt den Klimafaktor? (1940)
    In:  Landw. Jahrbuch 89:793-808.
    Details
    Publikationsdatum: 1940
    Beschreibung: Allgemeiner Bericht über Anpassungen der Landwirtschaft an das Klima, wie beispielsweise extensive und intensive Landwirtschaft, Fruchtfolge, Bodenbearbeitung, Frostschadenverhütung und Düngung. KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Schlagwort(e): Deutschland ; 1. Hälfte 20. Jahrhundert ; Anbautermine ; Boden ; Landwirtschaft ; Niederschlag ; Temperatur ; Verdunstung ; Wassermangel ; Düngung ; Frost ; Sonnenscheindauer
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 17
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    Beziehungen von Klima und Witterung zur Häufigkeit der Pflanzenkrankheiten in Schleswig-Holstein (1940)
    In:  Kühn-Archiv 54; p.403-430
    Details
    Publikationsdatum: 1940
    Beschreibung: Der Autor gibt die wichtigsten Schaderreger an Kulturpflanzen in Schleswig-Holstein an und begründet ihr mittleres Vorkommen mit den klimatischen Gegebenheiten der Region. Des Weiteren werden die Witterungsbedingungen der Jahre 1936-1938 genutzt, um die tatsächliche Häufigkeit des Auftretens der genannten Schaderreger zu erklären. In einem weiteren Abschnitt wird das regional unterschiedliche Auftreten von Schadorganismen mit den regionalen klimatischen Unterschieden in Schleswig-Holstein zu erklären versucht. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Schleswig-Holstein ; 1925-1938
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 18
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    Beziehung zwischen Klimafaktoren und Getreideerträgen auf Standorten der mittelschlesischen Ackerebene (1940)
    In:  Diss. Breslau
    Details
    Publikationsdatum: 1940
    Schlagwort(e): Schlesien
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 19
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    Deep focus earthquakes in America (1940)
    University of California Press
    In:  Pacific Science Association, 6th Congress Proceedings, vol. 1, Toronto, University of California Press, vol. 10, no. GL-TR-89-0230, pp. 149-150, (ISBN 3-933346-037)
    Details
    Publikationsdatum: 1940
    Schlagwort(e): Seismology ; Seismicity ; Hypocentral depth
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 20
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    Tests of the XP-46 Airplane in the N.A.C.A. Full-Scale Wind Tunnel (1940)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-05
    Beschreibung: An investigation has been conducted on a full-scale model of the proposed XP-46 airplane in the N. A. C. A. full-scale wind tunnel pursuant to the request of the Amy Air Corps, Materiel Division. The primary purpose of the investigation was to determine the optimum arrangement of the various component parts to obtain the maximum high speed and to provide adequate engine cooling. Additional tests included a determination of the stalling characteristics and the effectiveness of ailerons and elevators. The profile drag of the wing was ascertained by the momentum method; the location of the transition point on the wing and the critical compressibility velocities of the various airplane components were determined from surface pressure surveys.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Format: application/pdf
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  • 21
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    Stress distribution in and equivalent width of flanges of wide, thin-wall steel beams (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The use of different forms of wide-flange, thin-wall steel beams is becoming increasingly widespread. Part of the information necessary for a national design of such members is the knowledge of the stress distribution in and the equivalent width of the flanges of such beams. This problem is analyzed in this paper on the basis of the theory of plane stress. As a result, tables and curves are given from which the equivalent width of any given beam can be read directly for use in practical design. An investigation is given of the limitations of this analysis due to the fact that extremely wide and thin flanges tend to curve out of their plane toward the neutral axis. A summary of test data confirms very satisfactorily the analytical results.
    Materialart: NACA-TN-784
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 22
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    Application of the methods of gas dynamics to water flows with free surface I : flows with no energy dissipation (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The application is treated in sufficient detail to facilitate as much as possible its application by the engineer who is less familiar with the subject. The present work was undertaken with two objects in view. In the first place, it is considered as a contribution to the water analogy of gas flows, and secondly, a large portion is devoted to the general theory of the two-dimensional supersonic flows.
    Materialart: NACA-TM-934
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 23
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    Application of the Methods of Gas Dynamics to Water Flows with Free Surface II : Flows with Momentum Discontinuities (hydraulic Jumps) (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In this paper an introduction to shock polar diagrams is given which then leads into an examination of water depths in hydraulic jumps. Energy loss during these jumps is considered along with an extended look at elementary solutions of flow. An experimental test set-up is described and the results presented.
    Materialart: NACA-TM-935
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 24
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    Tests of Lead-bronze Bearings in the DVL Bearing-testing Machine (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The lead-bronze bearings tested in the DVL machine have proven themselves very sensitive to load changes as in comparison with bearings of light metal. In order to prevent surface injuries and consequently running interruptions, the increase of the load has to be made in small steps with sufficient run-in time between steps. The absence of lead in the running surface, impurities in the alloy (especially iron) and surface irregularities (pores) decreases the load-carrying capacity of the bearing to two or three times that of the static load.
    Materialart: NACA-TM-943
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 25
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    Materials for Slack Diaphragms (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report deals with systematic experiments carried out on five diaphragm materials with different pretreatment, for the purpose of ascertaining the suitability of such materials for slack diaphragms. The relationship of deflection and load, temperature and moisture, was recorded. Of the explored materials, synthetic leather, balloon cloth, goldbeaters skin, Igelit and Buna, synthetic leather treated with castor oil is the most suitable material for the small pressure range required. Balloon cloth is nearly as good, while goldbeaters skin, Igelit and Buna were found to be below the required standards.
    Materialart: NACA-TM-964
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 26
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    Corrections on the Thermometer Reading in an Air Stream (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A method is described for checking a correction formula, based partly on theoretical considerations, for adiabatic compression and friction in flight tests and determining the value of the constant. It is necessary to apply a threefold correction to each thermometer reading. They are a correction for adiabatic compression, friction and for time lag.
    Materialart: NACA-TM-956
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 27
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    General Relationships Between the Various Systems of Reference Axes Employed in Flight Mechanics (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The different possibilities of orientation of the systems of axes currently employed in flight mechanics are compiled and described. Of the three possible couplings between the wind and aircraft axes, the most suitable coupling is that in which the y axis is made the principal axis of rotation for one of the two coupling angles (angles of attack). In connection with this coupling, an experimental system of axes is introduced, whose axes x(sub e) and z(sub e) are situated in the plane of symmetry of the airplane and rotate about the airplane lateral axis y = y(sub e). This system of axes enables the utilization of the coefficients obtained in the wind tunnel in the flight-mechanic equations by a simple transformation, with the aid of the angle of attack, measured in the plane of symmetry of the airplane.
    Materialart: NACA-TM-958
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 28
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    Chordwise load distribution of a simple rectangular wing (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The chordwise distribution theory was taken over from the theory of the infinite wing. Since in this work a series expansion in b/t was used, the computation converges only for large aspect ratios. In this paper a useful approximate solution will be found also for wings with large chord - i.e., small aspect ratio.
    Materialart: NACA-TM-963
    Format: application/pdf
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  • 29
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    Consideration of auxiliary jet propulsion for assisting take-off (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-E-49
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 30
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    The Effect of Initial Displacement of the Center Support on the Buckling of a Column Continuous over Three Supports (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-L-256
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 31
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    Wind Tunnel Tests of a Submerged-engine Fuselage Design (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-L-485
    Format: application/pdf
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  • 32
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    Experimental Investigation to Determine the Relative Magnitude of Vertical and Horizontal Gusts in the Atmosphere (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-L-576
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 33
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    Effect of Fuel-Air Ratio, Inlet Temperature, and Exhaust Pressure on Detonation (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An accurate determination of the end-gas condition was attempted by applying a refined method of analysis to experimental results. The results are compared with those obtained in Technical Report no. 655. The experimental technique employed afforded excellent control over the engine variables and unusual cyclic reproducibility. This, in conjunction with the new analysis, made possible the determination of the state of the end-gas at any instant to a fair degree of precision. Results showed that for any given maximum pressure the maximum permissible end-gas temperature increased as the fuel-air ratio was increased. The tendency to detonate was slightly reduced by an increase in residual gas content resulting from an increase in exhaust backpressure with inlet pressure constant.
    Materialart: NACA-TR-699
    Format: application/pdf
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  • 34
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    Tensile Elastic Properties of Typical Stainless Steels and Nonferrous Metals as Affected by Plastic Deformation and by Heat Treatment (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A general discussion is given of the relationships between stress, strain, and permanent set. From stress-set curves are derived proof stresses based on five different percentages of permanent set. The influence of prior plastic extension on these values is illustrated and discussed. A discussion is given of the influence of work-hardening, rest interval, and internal stress on the form of the proof stress-extension curve.
    Materialart: NACA-TR-696
    Format: application/pdf
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  • 35
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    A theoretical study of lateral stability with an automatic pilot (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The influence of automatic operation of the aileron and rudder controls on the lateral stability of an airplane is discussed. The control deflections are assumed to be proportional to the deviations and to the rates of deviation of the airplane from steady-flight conditions. The effects of changes in the types of deviation governing control application are considered. For one simple method of control in which the aileron deflection is proportional to the angle of bank and the rudder deflection is proportional to the angle of yaw, the effect of lag in control application is studied and regions of stability with and without lag are given. For the simple control with lag, curves are included that show the variations in the roots of the stability equation with changes in the amount of control applied. It is concluded that, although the simple control provides a satisfactory means of varying most of the lateral stability characteristics, the stability in azimuth will always be poor for such a control.
    Materialart: NACA-TR-693
    Format: application/pdf
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  • 36
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    Effective Gust Structure at Low Altitudes as Determined from the Reactions of an Airplane (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Measurements of gust structure and gust intensity were made in the lower levels of the atmosphere (0 to 3,500 ft.). An Aeronca C-2 airplane was used as the measuring instrument, the gust structure being derived from the recorded motions of the airplane. Data were also obtained on wind velocities and temperatures as functions of altitude for use in attempting to correlate the gust-structure data with various meteorological quantities. The results indicated little or no correlation between the gust velocity and the gradient distance. The data, however, did indicate that an airplane the size of the Aeronca will respond most frequently to gusts having gradient distance of the order of 30 feet. The maximum true gust velocity measured during the investigation was 25 feet per second.
    Materialart: NACA-TR-692
    Format: application/pdf
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  • 37
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    Free-Spinning Wind-Tunnel Tests of a Low-Wing Monoplane with Systematic Changes in Wings and Tails V : Effect of Airplane Relative Density (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The reported tests are a continuation of an NACA investigation being made in the free-spinning wind tunnel to determine the effects of independent variations in load distribution, wing and tail arrangement, and control disposition on the spin characteristics of airplanes. The standard series of tests was repeated to determine the effect of airplane relative density. Tests were made at values of the relative-density parameter of 6.8, 8.4 (basic), and 12.0; and the results were analyzed. The tested variations in the relative-density parameter may be considered either as variations in the wing loading of an airplane spun at a given altitude, with the radii of gyration kept constant, or as a variation of the altitude at which the spin takes place for a given airplane. The lower values of the relative-density parameter correspond to the lower wing loadings or to the lower altitudes of the spin.
    Materialart: NACA-TR-691
    Format: application/pdf
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  • 38
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    Preliminary wind-tunnel investigation of an NACA 23012 airfoil with various arrangements of venetian-blind flaps (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of venetian-blind flaps to determine the aerodynamic section characteristics as affected by the over-all flap chord, the chords of the slats used to form the flap, the slat spacing, the number of slats and the position of the flap with respect to the wing. Complete section data are given in the form of graphs for all the combinations tested.
    Materialart: NACA-TR-689
    Format: application/pdf
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  • 39
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    The aileron as an aid to recovery from the spin (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: As part of a general investigation by the NACA of factors that affect the spin, the use of the aileron as an aid to recovery from the spin was studied. Tests of 10 different models, covering a wide range of mass distribution, were made in the NACA free-spinning tunnel to determine the effects of a large downward deflection of the outboard aileron and of normal angular deflections of the ailerons upon recovery characteristics. The results indicate that the direction of aileron setting, with or against the spin, which will aid recovery from the spin depends upon the airplane weight distribution. For monoplanes and for biplanes with lower-wing ailerons, ailerons with the spin will be favorable when the weight is distributed chiefly along the fuselage (single-engine airplanes) and ailerons against the spin will be favorable when the weight is distributed chiefly along the wings (multi engine airplanes). Downward movement of the outboard aileron through a large angle will not always be effective in aiding recovery, the effectiveness of such a movement also being dependent upon the weight distribution of the airplane.
    Materialart: NACA-TN-776
    Format: application/pdf
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  • 40
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    Ionization in the Knock Zone of an Internal-combustion Engine (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The ionization in the knock zone of an internal-combustion engine was investigated. A suspected correlation between the intensity of knock and the degree of ionization was verified and an oscillation in the degree of ionization corresponding in frequency to the knock vibrations in the cylinder pressure was observed.
    Materialart: NACA-TN-774
    Format: application/pdf
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  • 41
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    Chart for critical compressive stress of flat rectangular plates (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-773
    Format: application/pdf
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  • 42
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    Analysis of Cylinder-pressure-indicator Diagrams Showing Effects of Mixture Strength and Spark Timing (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was made to determine the effect of mixture strength and of normal as well as optimum spark timing on the combustion, on the cylinder temperature, and on the performance characteristics of an engine. A single-cylinder test unit utilizing an air-cooled cylinder and a carburetor and operating with gasoline having an octane rating of 92 was used. The investigation covered a range of fuel-air ratios from 0.053 to 0.118. Indicator diagrams and engine-performance data were taken for each change in engine conditions. Examination of the indicator shows that for fuel-air ratios less than and greater than 0.082 the rate and the amount of effective fuel burned decreased. For a fuel-air ratio of 0.118 the combustion efficiency was only 58 percent. Advancing the spark timing increased the rate of pressure rise. This effect was more pronounced with leaner mixtures.
    Materialart: NACA-TN-772
    Format: application/pdf
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  • 43
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    Transient Effects of the Wing Wake on the Horizontal Tail (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was made of the effect of the wing wake on the lift of the horizontal tail surfaces. In the development of expressions for this effect, the growth of wing circulation and wing wake, the time interval represented by the tail length, and the development of lift by the rail were considered. The theory has been applied to a specific case to show the magnitude of the effect to be expected. It is shown that, for motions below a certain frequency, the development of lift by the tail may be represented by a simple lag function. The lag is, however, somewhat greater than that indicated by the rail length.
    Materialart: NACA-TN-771
    Format: application/pdf
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  • 44
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    The Lateral Stability of Equal-flanged Aluminum-alloy I-beams Subjected to Pure Bending (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Equal-flange beams of a special extruded I-section of 27ST aluminum alloy were tested in pure bending. Complete end fixity was not attained. Loading was continued until a definite maximum value had been reached. Tensile tests were made on specimens cut from the flanges and the web of each beam. Compressive stress-strain characteristics were determined by pack compression tests on specimens cut from the flanges. Values computed from an equation previously suggested by one of the authors for the critical stress at which such beams become unstable were found to be in good agreement with values computed from experimentally determined critically bending moments.
    Materialart: NACA-TN-770
    Format: text
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  • 45
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    Spin Tests of a Low-lying Monoplane in Flight and in the Free-spinning Wind Tunnel (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Comparative full-scale and model spin tests were made with a low-lying monoplane in order to extend the available information as to the utility of the free-spinning wind tunnel as an aid in predicting full-scale spin characteristics. For a given control disposition the model indicated steeper spins than were actually obtained with the airplane, the difference being most pronounced for spins with elevators up. Recovery characteristics for the model, on the whole, agreed with those for the airplane, but a disagreement was noted for the case of recovery with elevators held full up. Free-spinning wind-tunnel tests are a useful aid in estimating spin characteristics of airplanes, but it must be appreciated that model results can give only general indications of full-scale behavior.
    Materialart: NACA-TN-769
    Format: application/pdf
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  • 46
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    Correlation of knocking characteristics of fuels in an engine having a hemispherical combustion chamber (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Data are presented to show the effects of inlet-air pressure, inlet-air temperature, and compression ratio on the maximum permissible performance obtained with having a hemispherical-dome combustion chamber. The five aircraft-engine fuels used have octane numbers varying from 90 to 100 plus 2 ml of tetraethyl lead per gallon. The data were obtained on a 5 1/4-inch by 4 3/4-inch liquid-cooled engine operating at 2,500 r.p.m. The compression ratio was varied from 6.0 to 8.9. The inlet-air temperature was varied from 110 to 310 F. For each set of conditions, the inlet-air pressure was increased until audible knock occurred and then reduced 2 inches of mercury before data were recorded. The results for each fuel can be correlated by plotting the calculated end-gas density factor against the calculated end-gas temperature. Measurements of spark-plugs, cutting off the switch to one spark plug lowered the electrode temperature of that plug from a value of 1,365 F to a value of 957 F. The results indicate that the surface temperatures of combustion-chamber areas which become new sources of ignition markedly increase after ignition.
    Materialart: NACA-TN-768
    Format: application/pdf
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  • 47
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    Cyclic Stress-strain Studies of Metals in Torsion (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-790
    Format: application/pdf
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  • 48
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    Extension of Pack Method for Compressive Tests (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The pack method for determining compressive stress-strain graphs described in NACA Report No. 649 has been modified to extend it's application to thinner gages and stronger materials. The principal modifications consisted in the provision of additional support against instability cementing the specimens of the pack together with fused shellac and the provision of special clamps to hold the specimens together while the test is in progress. The shellac was found to increase the buckling load of the pack without any appreciable effect on the compressive stress-strain graph of the material. The extended pack method described in this note has made possible the application of stresses in excess of 220 kips per square inch to sheet material having a thickness of only 0.02 inch.
    Materialart: NACA-TN-789
    Format: application/pdf
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  • 49
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    Drag Determination of the Forward Component of a Tricycle Landing Gear (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Wind-tunnel tests were performed to determine the drag of the front-wheel arrangements of several types of tricycle landing gear. One wheel was tested in arrangements to simulate both nonretracted and partially retracted types. The landing gears were tested in conjunction with a fuselage, and the effects of wheel extension and longitudinal location were determined. The drag changed very little with either longitudinal location or wheel extension for the landing gear with the lowest drag; a completely faired landing gear of the wheelspan, single-strut type. The drag of the trouser-type landing gear increased considerably, however, with an increase in the wheel extension. The wheel of the unaired retractable landing gear was at least one-half retracted into the fuselage before the drag became less than that of the best nonretracted landing gear. The drag per unit frontal area of the landing gears of the present tests was about the same as that found for similar landing gears in earlier tests.
    Materialart: NACA-TN-788
    Format: application/pdf
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  • 50
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    A study of the air movement in two aircraft-engine cylinders (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Studies were made of the air movements in the NACA glass-cylinder apparatus using cylinder heads similar to those on the Wright R-1820-G engine and the Pratt & Whitney Wasp engine as modified by the Eclipse Aviation Corporation to use fuel-injection equipment. The air movements were made visible by mixing small feathers with the air; high-speed motion pictures were than taken of the feathers as they swirled about the inside the glass cylinder. The test engine speeds were 350, 500, and 1,000 r.p.m. Motion pictures were also taken of gasoline sprays injected into the cylinder during the intake stroke. The air flow produced by each cylinder head is described and some results of the velocity measurements of feathers are presented. The apparent time intervals required for vaporization of the gasoline sprays are also given.
    Materialart: NACA-TN-766
    Format: application/pdf
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  • 51
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    The Effects of Engine Speed and Mixture Temperature on the Knocking Characteristics of Several Fuels (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Six 100-octane and two 87-octane aviation engine fuels were tested in a modified C.F.R. variable-compression engine at 1,500, 2,000 and 2,500 rpm. The mixture temperature was raised from 50 to 300 F in approximately 50 degree steps and, at each temperature, the compression ratio was adjusted to give incipient knock as shown by a cathode ray indicator. The results are presented in tabular form. The results are analyzed on the assumption that the conditions which determine whether a given fuel will knock are the maximum values of density and temperature reached by the burning gases. A maximum permissible density factor, proportional to the maximum density of the burning gases just prior to incipient knock, and the temperature of the burning gases at that time were computed for each of the test conditions. Values of the density factors were plotted against the corresponding end-gas temperatures for the three engine speeds and also against engine speed for several and end-gas temperatures. The maximum permissible density factor varied only slightly with engine speed but decreased rapidly with an increase in the end-gas temperature. The effect of changing the mixture temperature was different for fuels of different types. The results emphasize the desirability of determining the anti knock values of fuels over a wide range of engine and intake-air conditions rather that at a single set of conditions.
    Materialart: NACA-TN-767
    Format: application/pdf
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  • 52
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    A Method of Measuring Piston Temperatures (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A method that makes use of thermocouples has been developed to measure the temperature of engine pistons operating at high speeds. The thermocouples installed on the moving piston are connected with a potentiometer outside the engine by means of pneumatically operated plungers, which make contact with the piston thermocouples for about 10 crankshaft degrees at the bottom of the piston stroke. The equipment is operated satisfactory at engine speeds of 2,400 r.p.m. and shows promise of successful operation at higher engine speeds. Measurements of piston temperatures in a liquid-cooled compression-ignition engine and in an air-cooled spark-ignition are presented.
    Materialart: NACA-TN-765
    Format: application/pdf
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  • 53
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    Factors Affecting Heat Transfer in the Internal-combustion Engine (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-787
    Format: application/pdf
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  • 54
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    Structural Tests of a Stainless Steel Wing Panel by Hydrostatic Loading (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-786
    Format: application/pdf
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  • 55
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    Flight Investigation of Control-stick Vibration of the YG-1B Autogiro (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: As a preliminary step in an investigation of control-stick vibration in direct-control autogiros, the periodic variations in the moments transmitted through the control system of a YG-1B autogiro were recorded in flight. The results of the measurements are presented in the form of coefficients of Fourier series expressing the varying part of the lateral and the longitudinal moments acting between rotor and fuselage at the control trunnions. The most important component of the variation in stick force was found to have frequency of three times the rotor speed and an amplitude that rose from negligible values at tip-speed ratio below 0.20 to +/-5.2 pounds longitudinally and +/-3.2 pounds laterally at tip-speed ratios of 0.35. Variations in stick force at all other frequencies were small in comparison with those at three times the rotor speed.
    Materialart: NACA-TN-764
    Format: application/pdf
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  • 56
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    Wind-tunnel Investigation of Two Airfoils with 25-percent-chord Gwinn and Plain Flaps (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the overall chord and of an NACA 23015 airfoil with a plain flap having a 25-percent chord were conducted to determine the relative merits of the Gwinn and the plain flaps. The tests indicated that, based on speed-range ratios, the plain flap was more effective than the Gwinn flap. At small flap deflections, the plain flap had lower drag coefficients at lift-coefficient values less than 0.70. For lift coefficients greater than 0.70, however, the Gwinn flap at all downward flap deflections had the lower drag coefficients.
    Materialart: NACA-TN-763
    Format: application/pdf
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  • 57
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    Wind Tunnel Investigation of Fuselage Stability in Yaw with Various Arrangements of Fins (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was made in the 7-by-10 foot wind tunnel to determine the effects of dorsal-type fins and various arrangements of fins on the aerodynamic characteristics of a streamline circular fuselage. Comparative plots of the aerodynamic characteristics of the fuselage alone and the fuselage with various fin arrangements are given to show their effects on coefficients of yawing moment, drag, and lateral force. Results are also given for one case in which a rear fin on a circular fuselage was faired with modeling clay to obtain a fuselage shape with the same side elevation as the fuselage with the unfaired fin but with an elliptical cross section over the rearward portion of the fuselage. The results indicated that fin area to the rear of the center of gravity of the fuselage was beneficial in reducing the magnitude of the unstable yawing moments at large angles of yaw; whereas, fin area forward of the center of gravity was harmful. The dorsal-type fin was more effective for increasing the yawing stability of the fuselage than was a smoothly faired rearward portion with the same side elevation as the fuselage with the unfaired dorsal type fin. The minimum drag coefficient and the slope of the curve of yawing-moment coefficient of the fuselage at zero yaw were unaffected by the addition of the fins, within the experimental accuracy of the tests.
    Materialart: NACA-TN-785
    Format: application/pdf
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  • 58
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    The flow of a compressible fluid past a sphere (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The flow of a compressible fluid past a sphere fixed in a uniform stream is calculated to the third order of approximation by means of the Janzen-Rayleigh method. The velocity and the pressure distribution over the surface of the sphere are computed and the terms involving the fourth power of the Mach number, neglected in Rayleigh's calculation, are shown to be of considerable importance as the local velocity of sound is approached on the sphere. The critical Mach number, that is, the value of the Mach number at which the maximum velocity of the fluid past the sphere is just equal to the local velocity of sound, is calculated for both the second and the third approximation and is found to be, respectively, Mcr=0.587 and Mcr=0.573.
    Materialart: NACA-TN-762
    Format: application/pdf
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  • 59
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    Pressure-distribution investigation of an NACA 0009 airfoil with an 80-percent-chord plain flap and three tabs (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Pressure-distribution tests of an NACA 0009 airfoil with an 80-percent-chord plain flap and three plain tabs, having chord of 10, 20, and 30 percent of the flap chord, were made. Section data suitable for application to the design of horizontal and vertical tail surfaces were obtained. Resultant-pressure diagrams for the airfoil with the flap and the 20-percent-chord tab are presented. Plots are also given of increments of normal-force and hinge-moment coefficients for the airfoil, the flap, and the three tabs. A comparison of some characteristic slopes for the 30-, the 50-, and the 80-percent-chord flaps, tested in the general investigation of plain flaps for control surfaces, is included. Section aerodynamic and load data have been made available for a wide range of flap and a tab chords to be used on an NACA 0009 airfoil or on other conventional sections.
    Materialart: NACA-TN-761
    Format: application/pdf
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  • 60
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    A Full-scale Investigation of the Effect of Several Factors on the Shimmy of Cantering Wheels (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A full-scale investigation has been conducted to determine the effect of various factors on the shimmy of castering wheels. The factors considered were the geometric arrangement, the tire types, the variations of load, the spindle moment of inertia, and the tire inflation. A comparison of the results of the present investigation with those calculated from existing theory was made. The constants needed in the calculations to determine the damping required for a castering wheel were measured. The results indicate that solid friction appears to be impracticable as the sole damping agent for castering nose wheels on large airplanes. Also it was concluded that the existing theory is adequate for calculating the damping required to prevent shimmy. The caster angle and the spindle moment of inertia were found to influence the solid friction required to prevent shimmy. The effect of variations in the type and the pressure of the tire was insignificant.
    Materialart: NACA-TN-760
    Format: application/pdf
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  • 61
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    A Flight Investigation of Exhaust-heat De-icing (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The National Advisory Committee for Aeronautics conducted exhaust-heat de-icing tests in flight to provide data needed in the application of this method. The capacity to extract heat from the exhaust gas for de-icing purposes, the quantity of heat required, and other factors were examined. The results indicate that a wing-heating system employing a spanwise exhaust tube within the leading edge of the wing removed 30 to 35 percent of the heat from exhaust gas entering the wing. Data are given from which the heat required for ice prevention can be calculated. Sample calculations have been made on the basis of existing engine power/wing area ratios to show that sufficient heating can be obtained for ice protection on modern transportation airplanes, provided that uniform distribution of the heat can be secured.
    Materialart: NACA-TN-783
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  • 62
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    Measurements and Analysis of the Motion of a Canard Airplane Model in Gusts (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-758
    Format: application/pdf
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  • 63
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    Pressure-distribution investigation on an NACA 0009 airfoil with a 30-percent-chord plain flap and three tabs (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Pressure-distribution tests of an NACA 0009 airfoil with a 30-percent-chord plain flap and three plain tabs, having chords 10, 20, and 30 percent of the flap chord, were made. The purpose of these tests was to continue an investigation to supply structural and aerodynamic section data that may be applied to the design of horizontal and vertical tail surfaces. The results are presented as diagrams of resultant pressures and of resultant-pressure increments for the airfoil with the flap and the 20-percent-chord tab. Increments of normal-force and hinge-moment coefficients for the airfoil, the flap, and the three tabs are also given. At all unstalled flap and tab deflections, the experimental distributions agree well with those calculated by an analytical method. The agreement is poor, however, then the stalled or the unstalled condition of the flap or tab deflected alone was changed to an unstalled or stalled condition by the simultaneous deflection of both the flap and the tab.
    Materialart: NACA-TN-759
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  • 64
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    A study of unsymmetrical-loading conditions (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The force variation along the wing span under combined normal and angular accelerations is considered. Non dimensional curves of section load, shear, and moment are given for: (1) the air load that produces a normal acceleration; (2) the accompanying wing weight and normal inertia loads; (3) aileron and gust air loads that produce angular acceleration; (4) the angular inertia load of the wing. The required aerodynamic load distributions have been obtained by use of wing theory, and the wing inertia distributions are based on an analysis of wing-weight data. Several examples are included to illustrate the effect of wing taper and aileron span on the total shears and moments at any section along the span.
    Materialart: NACA-TN-757
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  • 65
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    The Effects of Piston-head Shape, Cylinder-head Shape, and Exhaust Restriction, on the Performance of a Piston-ported Two-stroke Cylinder (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-756
    Format: application/pdf
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  • 66
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    Wind tunnel tests of an NACA 23021 airfoil equipped with a slotted extensible and a plain extensible flap (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 airfoil equipped with two arrangements of a completely extended 15 percent chord extensible flap. One of the flaps had a faired juncture, without a gap; the other was provided with a slot between the trailing edge of the airfoil and the nose of the flap. The results showed that the basic airfoil gave the lowest profile-drag coefficients over the low lift range, the airfoil with the plain extensible flap gave the lowest profile-drag coefficients over the moderate lift range, and the airfoil with the slotted extensible flap gave the lowest profile-drag coefficients over the high lift range. The airfoil with the slotted extensible flap had the same maximum lift at a flap deflection of 25 degrees as the airfoil with the plain extensible flap had at a flap deflection of 60 degrees. The results of comparisons of the airfoil pitching-moment coefficients obtained with the two types of flap are dependent upon the basis chosen for comparison. Complete aerodynamic section characteristics are presented for the various flap deflections for both flap arrangements in the completely extended portion.
    Materialart: NACA-TN-782
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  • 67
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    Wind-tunnel investigation of an NACA 23030 airfoil with various arrangements of slotted flaps (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord slotted flap to determine the section aerodynamic characteristics of the airfoil affected by flap chord, slot shape, flap position, and flap deflection. The flap positions for maximum lift, the position for minimum drag at moderate and high lift coefficients, and the complete section aerodynamic characteristics of selected optimum arrangements are given. Envelope polar of various flap arrangements are included. The relative merits of slotted flaps of different chords on the NACA 23030 airfoil are discussed, and a comparison is made of each flap size with a corresponding flap size on the NACA 23021 and 23012 airfoils. The lowest profile drags at moderate lift coefficients were obtained with an easy entrance to the slot. The 25.66-percent-chord slotted flap gave lower drag than the 40-percent-chord flap for lift coefficients less than 1.8, but the 40-percent-chord flap gave considerably lower drag for lift coefficients. The drag coefficients at moderate and high lift coefficients were greater with both sizes of flap on the NACA 23030 airfoil than on either the NACA 23021 or the NACA 23012 airfoil. The maximum lift coefficient for the deflections tested with either flap was practically independent of airfoil.
    Materialart: NACA-TN-755
    Format: application/pdf
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  • 68
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    Mathematical analysis of aircraft intercooler design (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A mathematical analysis has been made to show the method of obtaining the dimensions of the intercooler that will use the least total power for a given set of design conditions. The results of this analysis have been used in a sample calculation and, on the basis of this calculation, a new inter cooler arrangement is suggested. Because the length of the two air passages of the new arrangement is short in comparison with the third dimension, the height of the intercooler, this intercooler arrangement has unusual dimensions. These dimensions give the proposed intercooler arrangement an advantage over one of usual dimensions because less total power will be consumed by the intercooler, the weight and volume of the intercooler will be smaller, and the pressure drop of both the engine air and the cooling air in passing through the intercooler will be lower.
    Materialart: NACA-TN-781
    Format: application/pdf
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  • 69
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    An Investigation of the Prevention of Ice on the Airplane Windshield (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation of three methods for the prevention and the removal of ice on an airplane windshield has been completed. The methods were: electric heating; hot-air heating; and an alcohol-dispensing, rotating wiper blade. The results showed that vision through the airplane windshield could be maintained during severe icing conditions by the use of heat. When put in operation prior to the formation of ice on the windshield the rotating wiper blade prevented the formation of ice. A combination of heated air and a rotating wiper blade would appear to protect against formation of ice on the windshield exterior, to prevent frost on the interior and to provide for the removal of rainfall.
    Materialart: NACA-TN-754
    Format: application/pdf
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  • 70
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    Measurement of the Forces Acting on Gliders in Towed Flight (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The magnitude, the direction, and the fluctuations of tow forces exerted upon gliders by towing them aloft behind an automobile were measured under a variety of conditions covering a range from gentle to severe types of operation. For these tests, the glider towing force did not exceed 1.6 of the gross weight of the glider. V-G records obtained during the towed-flight period as well as during the subsequent return glide to earth showed accelerations in the range from 3 to -1 g. The results of preliminary airplane tow tests are also presented.
    Materialart: NACA-TN-753
    Format: application/pdf
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  • 71
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    Measured moments of inertia of 32 airplanes (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A compilation of the experimentally determined moments of inertia of 32 airplanes is presented. The measurements were obtained at the laboratories of the naca by means of a pendulum method. The airplanes tested are representative of several types of aircraft of gross weight less than 10,000 pounds. The results are presented in coefficient as well as in dimensional form. An elementary analysis of the data disclosed the possibility of grouping the results according to wing type of the airplane, as low-wing monoplanes, parasol and high-wing monoplanes, and biplanes. The data are shown to provide a convenient means of rapidly estimating the moments of inertia of other airplanes. A three view drawing of each of the 32 airplanes is included.
    Materialart: NACA-TN-780
    Format: application/pdf
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  • 72
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    An Investigation of Sheet-stiffener Panels Subjected to Compression Loads with Particular Reference to Torsionally Weak Stiffeners (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A total of 183 panel specimens of 24ST aluminum alloy with nominal thickness of 0.020, and 0.040 inch with extruded bulb-angle sections of 12 shapes spaced 4 and 5 inches as stiffeners were tested to obtain the buckling stress and the amplitude of the maximum wave when buckled. Bulb angles from 3 to 27 1/2 inches long were tested as pin-end columns. The experimental data are presented as stress-strain and column curves and in tabular form. Some comparisons with theoretical results are presented. Analytical methods are developed that make it possible for the designer to predict with reasonable accuracy the buckling stress and the maximum-wave amplitude of the sheet in stiffened-panel combinations. The scope of the tests was insufficient to formulate general design criteria but the results are presented as a guide for design and an indication of the type of theoretical and experimental work that is needed.
    Materialart: NACA-TN-752
    Format: application/pdf
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  • 73
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    Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Two topics of interest to persons attempting to apply the heat method of preventing ice formation on aircraft are considered. Surfaces moving through air at high speed are shown, both theoretically and experimentally, to be subject to important aerodynamic heating effects that will materially reduce the heat required to prevent ice. Numerical calculations of the path of water drops in an air stream around a circular cylinder are given. From these calculations, information is obtained on the percentage of the swept area cleared of drops.
    Materialart: NACA-TN-779
    Format: application/pdf
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  • 74
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    Damping formulas and experimental values of damping in flutter models (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The problem of determining values of structural damping for use in flutter calculations is discussed. The concept of equivalent viscous damping is reviewed and its relation to the structural damping coefficient g introduced in NACA Technical Report No. 685 is shown. The theory of normal modes is reviewed and a number of methods are described for separating the motions associated with different modes. Equations are developed for use in evaluating the damping parameters from experimental data. Experimental results of measurements of damping in several flutter models are presented.
    Materialart: NACA-TN-751
    Format: application/pdf
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  • 75
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    A generalized vortex theory of the screw propeller and its application (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The vortex theory as presented by the author in earlier papers has been extended to permit the solution of the following problems: (1) the investigation of the relation between thrusts and torque distribution and energy loss as given by the induction of helical vortex sheets and by the parasite drag; (2) the checking of the theorem of Betz of the rigidly behaving helical vortex sheet of minimum induced energy loss; (3) the extension of the theory of the screw propeller of minimum energy loss for the inclusion of parasite-drag distribution along the blades. A simple system of diagrams has been developed to systematize the design of airplane propellers for a wide range of parasite-drag distribution along the blades.
    Materialart: NACA-TN-750
    Format: application/pdf
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  • 76
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    A New Method of Studying the Flow of the Water Along the Bottom of a Model of a Flying-boat Hull (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A new method of studying the flow of the water along the bottom of a model of a flying-boat hull is described. In this method, the model is fitted with a transparent bottom and is divided down the center line by a bulkhead. The flow is observed and photographed through one-half of the model by means of the diffused illumination from a battery of lamps contained in the other half of the model. Photographs of the flow, particularly of the changes that occur when the step ventilates, are shown. The results of the present investigation indicate that the method has considerable promise, chiefly in connection with motion-picture studies.
    Materialart: NACA-TN-749
    Format: application/pdf
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  • 77
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    Principles, practices, and progress of noise reduction in airplanes (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-748
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 78
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    Propeller rotation noise due to torque and thrust (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Sound pressure of the first four harmonics of rotation from a full-scale two-blade propeller were measured and are compared with values calculated from theory. The comparison is made (1) for the space distribution with constant tip speed and (2) for fixed space angles with variable tip speed. A relation for rotation noise from an element of radius developed by Gutin is given showing the effect of number of blades on the rotation noise.
    Materialart: NACA-TN-747
    Format: application/pdf
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  • 79
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    Notes on the stalling of vertical tail surfaces and on fin design (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A discussion is given of the important aspects of the stalling of vertical tail surfaces. The type of instability encountered is described and the possibilities of inadvertent occurrence are noted. The influence of directional flight tests on the behavior of a airplane when the tail stall takes place is discussed. In this connection, flight tests of a twin-engine airplane in which the vertical fin area was increased are cited. The reasons for inadequate directional stability in certain modern designs are accounted for and the properties and applications of dorsal fins are discussed. In addition, the chief factors regulating the requirements for conventional area are given, in which connection simplified criterion for directional stability is presented. It may be concluded that the stalling of vertical tail surfaces is not in itself a dangerous condition. Provided sufficient directional stability exists at large angles of sideslip, the tail stall may occur with modern airplanes, as with those of the past, without the knowledge or concern to the pilot.
    Materialart: NACA-TN-778
    Format: application/pdf
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  • 80
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    The frequencies of cantilever wings in beam and torsional vibrations (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Methods are described for calculating the period and frequency of vibration of cantilever wings and similar structures in which the weight and moment of inertia vary along the span. Both the beam and torsional frequencies may be calculated by these methods. The procedure is illustrated by examples. It is shown that a surprisingly close approximation to the beam frequency may be obtained by a very brief calculation in which the curvature of the wing in vibration is assumed to be constant. A somewhat longer computation permits taking account of the true curvature of the beam by a series of successive approximations which are shown to be strongly convergent. Analogous methods are applied to calculations of the torsional frequency. For the first approximation it is assumed that the angle of twist varies linearly alone the semispan. True variation of the twist is computed by successive approximations which are strongly convergent, as in the case of beam vibrations.
    Materialart: NACA-TN-746
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  • 81
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    Tests of a Gust-alleviating Flap in the Gust Tunnel (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests were made to determine the effectiveness of a long-period dynamically overbalanced flap in reducing airplane accelerations due to atmospheric gusts. For two gust shapes, one gust velocity, one forward velocity, and one wing loading, a series of flights was made with the flap locked and was then repeated with the flap free to operate. The records were evaluated by routine methods. The results indicate that the flap reduced the maximum acceleration increment 39 percent for a severe gust but with a representative gust shape (a sharp-edge gust), the reduction was only 3 percent. The results also indicate that the flap tended to reduce the longitudinal stability of the airplane. Computations made of the effectiveness and the action of the flap were in good agreement with the experimental results.
    Materialart: NACA-TN-745
    Format: application/pdf
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  • 82
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    The Development of Electrical Strain Gages (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The design, construction, and properties of an electrical-resistance strain gage consisting of fine wires molded in a laminated plastic are described. The properties of such gages are discussed and also the problems of molding of wires in plastic materials, temperature compensation, and cementing and removal of the gages. Further work to be carried out on the strain gage, together with instrument problems, is discussed.
    Materialart: NACA-TN-744
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  • 83
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    Internal-flow systems for aircraft (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation has been made to determine efficient arrangements for an internal-flow system of an aircraft when such a system operates by itself or in combination with other flow systems. The investigation included a theoretical treatment of a problem and tests in the NACA 5-foot vertical wind tunnel of inlet and outlet openings in a flat plate and in a wing. When an internal-flow system tends to decrease the final velocity of it's wake, the results showed that it should be arranged in series with the propulsive system; the inlet opening should be located at a forward stagnation point; and the outlet opening should be so shaped and located as to recover the kinetic energy of the jet without increasing the drag of other portions of the aircraft. When an internal-flow system tends to increase the final velocity new b's wake, as does a propeller, location of the inlet opening in the boundary layer or in the wake of the wing or in the fuselage may be desirable.
    Materialart: NACA-TN-777
    Format: application/pdf
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  • 84
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    Analysis of wind-tunnel data on directional stability and control (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-775
    Format: application/pdf
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  • 85
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    Aerodynamics of Rotating-wing Aircraft with Blade-pitch Control (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In the present report, with the aid of the usual computation methods, a rotor is investigated the pitch of whose blades is capable of being controlled in such a manner that it varies linearly with the flapping angle. To test the effect of this linkage on the aircraft performance, the theory is applied to an illustrative example.
    Materialart: NACA-TM-929
    Format: application/pdf
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  • 86
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    Theoretical and experimental investigations of the drag of installed aircraft radiators (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The present report proposes the determination of the absolute magnitude of the total radiator drag and, in addition, of the different causes of the radiator drag.
    Materialart: NACA-TM-932 , International Congress for Applied Mechanics (5th : 1938 : Cambridge, Massachusetts)
    Format: application/pdf
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  • 87
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    The Torsion of Box Beams with One Side Lacking (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The torsion of box beams of rectangular section, the edges of which are strengthened by flanges, and of which one side is lacking, is analyzed by the energy method. The torsional stresses are generally taken up by the bending of the two parallel walls, the rigidity of which is augmented by the third wall. The result was checked experimentally on duralumin and plywood boxes. The torsion recorded was 10 to 30 percent less than that given by the calculation, owing to self-stiffening.
    Materialart: NACA-TM-939
    Format: application/pdf
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  • 88
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    Some data on the static longitudinal stability and control of airplanes : design of control surfaces (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In the solution of a number of problems on the stability and controllability of airplanes, there arises the necessity for knowing the characteristics of the tail surfaces of the types in common use today. Of those characteristics, the most important are the effectiveness and hinge moments of the tail surfaces. As has been shown in the present paper, there exists the possibility of determining these characteristics by the formulas obtained with a degree of accuracy sufficient for the purposes of preliminary computation. These formulas take into account a number of fundamental tail characteristics such as tail cut-outs on the control surface and the form of the control surface leading edge.
    Materialart: NACA-TM-941
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  • 89
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    The lead susceptibility of fuels and its dependence on the chemical composition (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The fact that by the use of tetraethyl lead a number of otherwise unsuitable fuels could be made to meet engine requirements was not sufficiently appreciated. While use of tetraethyl lead is limited, the addition of special leaded fuels that increase the octane number is a requirement for many fuels. In this connection, the extent to which the action of tetraethyl lead through the addition of knock-resistant hydrocarbons to the base gasoline is influenced, is quite important. To the elucidation of this problem and of the storage stability of leaded fuels, the present report is dedicated.
    Materialart: NACA-TM-940
    Format: application/pdf
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  • 90
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    On the theory of unsteady planing and the motion of a wing with vortex separation (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The disturbance imparted to water by a planing body give rise to a wave form of motion on the free surface, the length of the waves increasing indefinitely with increase in the Froude number and being directly proportional to the latter in the case of the plane or two-dimensional problem. At large Froude numbers the effect of the weight shows up to any appreciable extent only at some distance from the body, so that the flow near the body can be considered as part of a flow of an infinitely extending weightless fluid. This paper is a consideration of these characteristics as well as a formulation of the planing problem and its relation to the problem of a thin wing.
    Materialart: NACA-TM-942
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  • 91
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    Experimental Results with Airfoils Tested in the High-speed Tunnel at Guidonia (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The results are presented of a triple series of tests using force measurements, pressure-distribution measurements, and air flow photographs on airfoil sections suitably selected so that comparison could be made between the experimental and theoretical results. The comparison with existing theory is followed by a discussion of the divergences found, and an attempt is made to find their explanation.
    Materialart: NACA-TM-946
    Format: application/pdf
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  • 92
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    The Maximum Delivery Pressure of Single-stage Radial Superchargers for Aircraft Engines (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: With the aid of simple considerations and test results, an attempt is made to clear up some obscure points that still exist. The considerations are restricted to those cases where it is in fact of advantage to"force" the large delivery heads required for high altitude and high supercharge with a single-stage supercharger.
    Materialart: NACA-TM-949
    Format: application/pdf
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  • 93
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    Wind Tunnel Tests of Air Inlet and Outlet Openings on a Streamline Body (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-L-300
    Format: application/pdf
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  • 94
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    Requirements for unit fuel-injection systems (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-E-50
    Format: application/pdf
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  • 95
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    Preliminary Tests in the NACA Tank to Investigate the Fundamental Characteristics of Hydrofoils (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-WR-L-766
    Format: application/pdf
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  • 96
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    The calculated effect of various hydrodynamic and aerodynamic factors on the take-off of a large flying boat (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Report presents the results of an investigation made to determine the influence of various factors on the take-off performance of a hypothetical large flying boat by means of take-off calculations. The factors varied in the calculations were size of hull (load coefficient), wing setting, trim, deflection of flap, wing loading, aspect ratio, and parasite drag. The take-off times and distances were calculated to the stalling speeds and the performance above these speeds was separately studied to determine piloting technique for optimum take-off.
    Materialart: NACA-TR-702
    Format: application/pdf
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  • 97
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    Design charts relating to the stalling of tapered wings (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An aid in airplane design, charts have been prepared to show the effects of wing taper, thickness ratio, and Reynolds number on the spanwise location of the initial stalling point. Means of improving poor stalling characteristics resulting from certain combinations of the variables have also been considered; additional figures illustrate the influence of camber increase to the wing tips, washout, central sharp leading edges, and wing-tip slots on the stalling characteristics. Data are included from which the drag increases resulting from the use of these means can be computed. The application of the data to a specific problem is illustrated by an example.
    Materialart: NACA-TR-703
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  • 98
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    Preliminary Investigation of the Flying Qualities of Airplanes (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The National Advisory Committee for Aeronautics is undertaking an investigation of the flying qualities of airplanes. The work consists in the determination of the significant qualities susceptible of measurement, the development of the instruments required to make the measurements, and the accumulation of data on the flying qualities of existing airplanes, which data are to serve as a basis for quantitative specifications for the flying qualities of future designs. A tentative schedule of measurable flying qualities has been prepared and the instruments needed for their measurements have been assembled. A trial of the schedule and the instruments has been made using the Stinson SR-8e airplane. The results showed that, although the original schedule and instruments are basically satisfactory some further development is required to eliminate nonessential items and to expedite flight testing. The report describes and discusses the work done with this airplane.
    Materialart: NACA-TR-700
    Format: application/pdf
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  • 99
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    Investigations on the Incompletely Developed Plane Diagonal-Tension Field (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation on the incompletely developed diagonal-tension field. Actual diagonal-tension beams work in an intermediate stage between pure shear and pure diagonal tension; the theory developed by wagner for diagonal tension is not directly applicable. The first part of the paper reviews the most essential items of the theory of pure diagonal tension as well as previous attempts to formulate a theory of incomplete diagonal tension. The second part of the paper describes strain measurement made by the N. A. C. A. to obtain the necessary coefficients for the proposed theory. The third part of the paper discusses the stress analysis of diagonal-tension beams by means of the proposed theory.
    Materialart: NACA-TR-697
    Format: application/pdf
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  • 100
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    Piston Temperatures in an Air-Cooled Engine for Various Operating Conditions (1940)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: As part of a program for the study of piston cooling, this report presents the results of tests conducted on a single-cylinder, air-cooled, carburetor engine to determine the effect of engine operating conditions on the temperatures at five locations on the piston.
    Materialart: NACA-TR-698
    Format: application/pdf
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