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  • 1
    facet.materialart.
    Unbekannt
    In:  Geophysics, Milano, Gustav Fischer, vol. 1, no. 3, pp. 252-256, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Applied geophysics ; Amplitude ; Seismics (controlled source seismology)
    Standort Signatur Erwartet Verfügbarkeit
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  • 2
    facet.materialart.
    Unbekannt
    In:  Beiträge zur angewandten Geophysik, Milano, Gustav Fischer, vol. 6, no. 3, pp. 125-140, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Applied geophysics ; Seismics (controlled source seismology)
    Standort Signatur Erwartet Verfügbarkeit
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  • 3
    facet.materialart.
    Unbekannt
    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 47, no. 3, pp. 306-307, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Tectonics ; CRUST ; Earth model, also for more shallow analyses ! ; Plate tectonics
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
    facet.materialart.
    Unbekannt
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 47, no. 3, pp. 73-131, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Waves ; Seismology ; Review article
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
    facet.materialart.
    Unbekannt
    In:  Science, Milano, Gustav Fischer, vol. 83, no. 3, pp. 183-185, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Seismology ; Magnitude ; Energy (of earthquakes)
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
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    Unbekannt
    In:  Physics, Luxembourg, Conseil de l'Europe, vol. 7, no. B4, pp. 195-202, pp. B04202, (ISSN: 1340-4202)
    Publikationsdatum: 1936
    Schlagwort(e): Source ; Dislocation ; Elasticity
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
    facet.materialart.
    Unbekannt
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 46, no. 3, pp. 198-201, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Seismology ; mathematics ; geometry
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
    facet.materialart.
    Unbekannt
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 26, no. 3, pp. 341-390, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Seismology ; Hypocentral depth ; BSSA
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
    facet.materialart.
    Unbekannt
    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 83, no. 3, pp. 341, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Seismology ; Seismicity ; Hypocentral depth
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
    facet.materialart.
    Unbekannt
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 26, no. 3, pp. 111-117, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Micro seismicity ; NOISE ; BSSA
    Standort Signatur Erwartet Verfügbarkeit
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  • 11
    facet.materialart.
    Unbekannt
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 47, no. 3, pp. 1587-1610, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publikationsdatum: 1936
    Schlagwort(e): Tectonics ; CRUST ; Earth model, also for more shallow analyses ! ; Plate tectonics
    Standort Signatur Erwartet Verfügbarkeit
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  • 12
    facet.materialart.
    Unbekannt
    In:  Zeitschrift für Pflanzenernährung, Düngung und Bodenkunde 2 (47): 127-166
    Publikationsdatum: 1936
    Beschreibung: Auswertung von Lysimeter, Gefäß- und Versuchsstandorten, um Wasserverbrauch, aber auch Wasserhaltekapazität verschiedener Böden zu bestimmen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Berlin-Dahlem ; 1935
    Standort Signatur Erwartet Verfügbarkeit
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  • 13
    facet.materialart.
    Unbekannt
    In:  Diss. Halle (Saale), Kühn-Archiv, Band 42, 1936
    Publikationsdatum: 1936
    Beschreibung: Rangordnungsmethode nach Holdefleiß zur qualitativen Ertragsanalyse, Untersucht wurden die Erträge von Roggen, Weizen, Gerste, Hafer, Erbsen, Pferdebohnen, Hackfrüchte, Rübensamen, Zuckerrüben, Futterrüben, Kartoffeln KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag KATASTER-DETAIL: Delta Sonn (Winter) +, dann Ertrag (Roggen und Weizen) +; Delta T (Winter, September bis März) + und Delta T (Mai, Juni) -, dann Ertrag (Gerste) +; Delta Sonn (Winter) +, dann Ertrag (Sommergetreide) +; Delta T (April, Mai) - und Delta Nied (April, Mai) +, dann Ertrag (Weizen) +; Delta T (Mai bis Juli) - und Delta Nied (Mai bis Juli) +, dann Ertrag (Gerste) +; Delta Nied (April bis Juni) -, dann Ertrag (Hafer) -; Delta Sonn (März) +, dann Ertrag (Hafer) +; Delta Sonn (März) + und Delta T (Mai bis Erntezeit) -, dann Ertrag (Viktoria-Erbse) +; Delta Sonn (Winter) + und Delta Nied (Sommer) +, dann Ertrag (Pferdebohnen) +; Delta Nied +, dann Ertrag (Hackfrüchte) +; Delta Sonn (März, April) +, dann Ertrag (Zuckerrüben) +; Delta Sonn (Winter) +, dann Ertrag (Futterrüben) +; Delta T (September, Oktober - Vorjahr) + und Delta Nied (September, Oktober - Vorjahr) -, dann Ertrag (Kartoffeln) +; Delta Sonn (Winter) +, dann Ertrag (Kartoffeln) +; Delta Nied (April bis Agust) +, dann Ertrag (Kartoffeln) +;
    Schlagwort(e): Eichsfeld und Thüringer Becken ; 1900-1931 ; Ertrag ; Getreide ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Trockenheit ; Wassermangel ; Witterung
    Standort Signatur Erwartet Verfügbarkeit
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  • 14
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    Unbekannt
    In:  Mitteilungen für die Landwirtschaft 51(Heft 46).
    Publikationsdatum: 1936
    Beschreibung: Beobachtungen zum Ernteausfall und dessen Beeinflussung durch den Witterungsverlauf im Jahr 1936. Vergleich mit vergangenen Jahren. KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperatur und Niederschlag in den Monaten April, Mai und Juni und den Reichsertragsschätzungen, bzw. den tatsächlichen Erträgen. Bedeutung eines längeren warmen und niederschlagsarmen Junis für Getreide. KATASTER-DETAIL: Delta T (Juni) -, dann Erträge + Delta T (Juni) + und Niederschlage -, dann Ersträge -
    Schlagwort(e): Deutschland ; 1930-1936 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit
    Standort Signatur Erwartet Verfügbarkeit
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  • 15
    facet.materialart.
    Unbekannt
    In:  Monthly Notices Roy. astr. Soc., Geophys. Suppl., Kunming, China, D. Reidel Publishing Company, vol. 3, no. 7, pp. 380-388, pp. L09303, (ISSN: 1340-4202)
    Publikationsdatum: 1936
    Schlagwort(e): Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Elasticity ; Dislocation
    Standort Signatur Erwartet Verfügbarkeit
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  • 16
    facet.materialart.
    Unbekannt
    U. S. Coast and Geodetic Survey
    In:  Bull., Polar Proj. OP-O3A4, Earthquake investigations in California, 1934-35, 231 pp., London, U. S. Coast and Geodetic Survey, vol. 201, no. XVI:, pp. 163-225, (ISBN: 3-540-23712-7)
    Publikationsdatum: 1936
    Schlagwort(e): Spectrum ; Seismology ; Seismicity
    Standort Signatur Erwartet Verfügbarkeit
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  • 17
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2006-10-26
    Schlagwort(e): unknown
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 18
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-253
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 19
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-565
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 20
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This report was made to study the velocity distribution in an open, in a partially open, and in a partially expanding jet. The open-jet observations reveal minor systematic discrepancies from Tollmien's theoretical velocity distribution. The shearing-stress distribution for the partially open jet was determined. The value derived for the ratio of mixing distance to jet width was found to be in close agreement with the corresponding value for the open-jet boundary. The streamline pattern in a partially expanding channel was obtained from the observed velocity distribution and plotted, after which the distribution of the mixing distance for this case was also ascertained.
    Materialart: NACA-TM-789
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 21
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The present report examines the problem of ice formation from the point of view of the pilot and the meteorologist. Their experiences prove the ice deposit to be first and foremost a navigational problem and only secondarily a question of de-icing devices. With correct utilization of the meteorological information by the flyer, ice hazard can in many cases be minimized or avoided. Ice formation and the different types of ice deposits are listed and discussed. Weather formation during these ice deposits are also discussed as well as the effect of ice formation on aircraft.
    Materialart: NACA-TM-786
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 22
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: To investigate the process of ignition and combustion in the case of spray injection into heated air, a new form of apparatus is developed and the tests carried out with it described. Photographs of the spray before and after ignition are obtained at frequencies of 500 pictures per second. Pressures and temperatures are simultaneously recorded on oscillograms. Information on the initial conditions, ignition time lag, period of complete combustion, place where ignition starts, and general course of the combustion is obtained.
    Materialart: NACA-TM-790
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 23
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This study will be concerned with the critical examination of two main questions, mainly, susceptibility of centering and more generally, the conditions of static stability, longitudinal equilibrium, and the question of dynamic stability, or at least the damping of longitudinal vibrations about a position of equilibrium that may result from a small variation in the angle of attack.
    Materialart: NACA-TM-794
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 24
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Investigations on the flow phenomena at plates and cambered models were carried out with the aid of force measurements, some pressure distribution measurements, and photographic observation. The experimental methods are described and the results given. Section III of this work gives a comprehensive account of the results and enables us to see how nearly the lift line and lift surface theories agree with the experimental results.
    Materialart: NACA-TM-798
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 25
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Wind tunnel construction and design is discussed especially in relation to subsonic and supersonic speeds. Reynolds Numbers and the theory of compressible flows are also taken into consideration in designing new tunnels.
    Materialart: NACA-TM-808 , Volta Congress (5th : 1935 : Rome, Italy)
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 26
    Publikationsdatum: 2019-06-28
    Beschreibung: The report studies the problem of the transport of vorticity or of momentum in light of the Taylor and Prandtl theories which are briefly reviewed. It also show how the formulas of Prandtl could be brought into agreement with experimental results in those cases where they agree with the principle of statistic similitude of Karman, and particularly in the problem of the distribution of velocity and temperature in the wake of a heated cylindrical obstacle.
    Materialart: NACA-TM-799
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 27
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The present report contains a set of charts developed for computing the fixity effect on a compression member in a truss through its adjacent members, the amount of fixity being considered variable with the particular total truss load. The use of the charts is illustrated on two- and three-bay systems, as well as on a triangular truss.
    Materialart: NACA-TM-800
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 28
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA variable-density wind tunnel to provide information regarding the effects of aerodynamic interference between wings and fuselages at a large value of Reynolds number.
    Materialart: NACA-TR-540
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 29
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of wind tunnel tests of a wing in combination with each of three sizes of Fowler flap. The purpose of the investigation was to determine the aerodynamic characteristics as affected by flap chord and position, the air loads on the flaps, and the effect of flaps on the downwash.
    Materialart: NACA-TR-534
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 30
    Publikationsdatum: 2019-06-28
    Beschreibung: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Materialart: NACA-AR-21
    Format: application/pdf
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  • 31
    Publikationsdatum: 2019-06-28
    Beschreibung: This report deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined. The "Friedrichs-Von Karman equations" are shown to require the least amount of labor. Numerical examples by the several methods of analysis are given and the agreement between the calculation and experiment is shown.
    Materialart: NACA-TR-508
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 32
    Publikationsdatum: 2019-06-28
    Beschreibung: This report gives the results of an investigation conducted in the NACA full-scale wind tunnel on a small parasol monoplane equipped with three different split trailing-edge wing flaps. The object of the investigation was to determine and correlate data on the characteristics of the airplane and flaps as affected by variation in flap chord, flap deflection, and flap location along the wing chord. The results give the lift, the drag, and the pitching moment characteristics of the airplane, and the flap forces and moments, the pressure distribution over the flaps and wing at one section, and the downwash characteristics of the flap and wing combinations.
    Materialart: NACA-TR-539
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 33
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: A resume of the equations and formulas for the forces and moments on an aircraft-engine mount is presented. In addition, available experimental data have been included to permit the computation of these forces and moments. A sample calculation is made and compared with present design conditions for engine mounts.
    Materialart: NACA-TN-587
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 34
    Publikationsdatum: 2019-06-28
    Beschreibung: It is shown that the control force of ordinary ailerons may be reduced to zero over a range of deflections and at a given flight condition by the use of an appropriate differential movement. Approximations to the ideal motion obtainable with a simple linkage are discussed and a chart that enables the selection of an appropriate crank arrangement is presented. Various aspects of the practical application of the system are discussed and it is concluded that a small fixed tab, deflected to trim both ailerons upward, would be advantageous.
    Materialart: NACA-TN-586
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 35
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The development of metal construction for aircraft has created a need for accurate and detailed information regarding the strength of riveted joints in aluminum-alloy structures. To obtain this information the National Bureau of Standards in cooperation with the National Advisory Committee for Aeronautics is investigating the strength of riveted joints in aluminum alloys. The strength of riveted joints may be influenced by the form of the head, the ratio of the rivet diameter to the sheet thickness, the driving stress, and other factors. This note gives the results of tests to develop the riveting technique for test specimens and to determine the effects of these factors.
    Materialart: NACA-TN-585
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 36
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Many technical papers on the various phases of airplane take-off have been published. Frequently, however, there appear new ideas which affect only particular scattered phases of the subject and which do not receive individual publication. It is the purpose of this paper to present several ideas of this nature which may be of considerable aid in calculating take-off performance and one idea which should correct what appears to be a popular misconception of the importance of static propeller thrust. Although these considerations all concern the general problem of take-off, they are not directly related and therefore will be treated in individual sections.
    Materialart: NACA-TN-557
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 37
    Publikationsdatum: 2019-06-28
    Beschreibung: The results of tests made to determine the performance of a DePalma-Roots supercharger are presented. The performance of the DePalma supercharger with atmospheric pressure at the discharge was compared with that of a hypothetical NACA Roots-type supercharger of the same displacement. The tests were conducted at speeds from 1,000 to 6,000 r.p.m. and at pressure differences from 0 to 15 inches of mercury. The variation in clearance between the impeller tips and the impeller housing was determined for the DePalma supercharger at a speed of 2,000 r.p.m. and for the NACA supercharger at speeds from 500 to 3,000 r.p.m. with the pressure differences for each supercharger varying form 0 to 15 inches of mercury. The results indicate that, if warping and growing of the metals of the case and impellers are neglected, the most uniform clearances can probably be maintained for all operating conditions when the case and impellers are constructed of metals that have the same coefficient of expansion. The results also show that the discharge and intake openings of this model of the DePalma supercharger are too small, which lowers the volumetric efficiency and impairs the performance at all speeds and pressure differences. At high pressure difference the volumetric efficiency of the DePalma supercharger is greater when the discharge pressure surpasses atmospheric pressure than when the discharge pressure is atmospheric.
    Materialart: NACA-TN-558
    Format: application/pdf
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  • 38
    Publikationsdatum: 2019-06-28
    Beschreibung: The work of collecting acceleration data for racing airplanes during races, started in January 1934, has been continued by obtaining similar data in the airplanes winning first and second places in the 1935 Thompson Trophy Race. Records were taken in the Howard Racer "Mr. Mulligan" and in the Wittman D-12 Racer. The maximum positive accelerations were generally smaller than those recorded in other airplanes during earlier races; the maximum in the Howard Racer was 2.8 g, and one value of 4.25 g was obtained in the Wittman Racer. Minimum values were as low as -0.55 g in the Howard Racer and 0.3 g in the Wittman Racer.
    Materialart: NACA-TN-556
    Format: application/pdf
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  • 39
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Systematic flight investigation of the spinning characteristics of various airplanes over a period of several years have given the pilots engaged in the testing a varied and extensive experience. From this experience certain general rules of procedure have been formulated, particularly for the sequence of operation of the controls in recovery from spins, and are recommended to the attention of all pilots.
    Materialart: NACA-TN-555
    Format: application/pdf
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  • 40
    Publikationsdatum: 2019-06-28
    Beschreibung: Flight tests of a Grumman Scout (XSF-2) airplane fitted with a Pratt & Whitney 1535 supercharged engine were conducted to determine the effect of engine power, mass flow of the cooling air, and atmospheric temperature on cylinder temperature. The tests indicated that the difference in temperature between the cylinder wall and the cooling air varied as the 0.38 power of the brake horsepower for a constant mass flow of cooling air, cooling-air temperature, engine speed, and brake fuel consumption. The difference in temperature was also found to vary inversely as the 0.39 power of the mass flow for points on the head and the 0.35 power for points on the barrel, provided that engine power, engine speed, brake fuel consumption, and cooling-air temperature were kept constant. The results of the tests of the effect of atmospheric temperature on cylinder temperature were inconclusive owing to unfavorable weather conditions prevailing at the time of the tests. The method used for controlling the test conditions, however, was found to be feasible.
    Materialart: NACA-TN-584
    Format: application/pdf
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  • 41
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The circular motion for airship-like bodies has thus far been calculated only for a prolate ellipsoid of revolution (reference 1, p.133 and reference 2). In this paper, however, the circular motion of elongated bodies of revolution more nearly resembling airships will be investigated. The results will give the effect of rotation on the pressure distribution and thus yield some information as to the stresses set up in an airship in circular flight.
    Materialart: NACA-TN-554
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  • 42
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The distribution of the fuel among the various cylinders of a Pratt and Whitney 1340 S1H1-G engine was determined by chemically analyzing samples of exhaust gas from each cylinder. The engine was operated in the 20-foot wind tunnel at different power outputs, specific fuel consumptions, and engine speeds. The results showed that the variation in the quality of the mixture among the different cylinders was approximately 4 percent and was independent of power output, specific fuel consumption, and engine speed. The results also showed that the top cylinders operated with a lower air-fuel ratio than the bottom cylinders.
    Materialart: NACA-TN-583
    Format: application/pdf
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  • 43
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The proper landing of airplanes equipped with flaps, although probably no more difficult than landing without them, requires a different technique. The effects of flaps on the aerodynamics characteristics of a wing are given and, with the aid of figures and diagrams, a detailed comparison of the glide and landing of an airplane with and without flaps is made. The dangers attending improper execution and the importance of such factors as air speed fuselage attitude, glide-path angle, and control manipulation, upon all of which a pilot bases his judgement, are emphasized. Of most importance in connection with the use of flaps are: the maintenance of a sufficient margin of speed above the stall; a decisive use of the controls at the proper time; more cautious use of power during the approach glide; and, above all, the willingness to accept the steep nose-down attitude necessary in the glide resulting from the use of flaps.
    Materialart: NACA-TN-553
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  • 44
    Publikationsdatum: 2019-06-28
    Beschreibung: Preliminary tests have been made for the purpose of obtaining a flap arrangement suitable for direct and immediate control of the steepness of the glide path of an airplane, a use for which present flaps are not satisfactory. An attempt has been made to develop a flap giving a reasonably high maximum lift coefficient with relatively low deflection and maintaining this value of the maximum lift coefficient with a large increase of deflection, the increase in deflection being accompanied by a large increase in drag. An arrangement was found that gave a maximum lift coefficient of approximately 1.90 for all flap deflections between 25 and 80 degrees, within which range the drag of the wing increased regularly to a large value.
    Materialart: NACA-TN-552
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  • 45
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: An analysis is made of the autogiro jump take-off, in which the kinetic energy of the rotor turning at excess speed is used to effect a vertical take-off. By the use of suitable approximations, the differential equation of motion of the rotor during this maneuver is reduced to a form that can be solved. Only the vertical jump was studied; the effect of a forward motion during the jump is discussed briefly. The results of model tests of the jump take-off have been incorporated in the paper and used to establish the relative accuracy of the results predicted from the analysis. Good agreement between calculation and experiment was obtained by making justifiable allowances.
    Materialart: NACA-TN-582
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  • 46
    Publikationsdatum: 2019-06-28
    Beschreibung: The results of tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise are given in charts and are compared with results from tests of more conventional hulls. Increasing the angle of dead rise from 15 to 25 degrees: had little effect on the hump resistance; increased the resistance throughout the planning range; increased the best trim angle; reduced the maximum positive trimming moment required to obtain best trim angle; and had but a slight effect on the spray characteristics. For approximately the same angles of dead rise the resistance of the pointed-step hulls were considerably lower at high speeds than those of the more conventional hulls.
    Materialart: NACA-TN-551
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  • 47
    Publikationsdatum: 2019-06-28
    Beschreibung: An analysis of the factors governing the oscillation of an autogiro rotor blade in the plane of the rotor disk showed that the contribution of the air forces to the resultant motion was small and that the oscillation is essentially a direct effect of the rotor-blade flapping motion. A comparison of calculated oscillations with those measured in flight on three different rotors disclosed that the calculations gave satisfactory agreement with experiment. The calculated air forces on the rotor blade appear to be larger than the experimental ones, but this discrepancy can be attributed to the deficiencies in the strip analysis.
    Materialart: NACA-TN-581
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  • 48
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Measurements were made to determine the relative maximum forces a pilot can exert on the controls of an airplane with the view of obtaining systematic data upon which to base the location of controls within the cockpit and the design of the control surfaces. A cockpit model of generous proportions, capable of being rotated to any attitude, was built with the location of the control stick and rudder pedals adjustable over a wide range of positions with respect to the seat. Besides measurements of maximum forces obtainable with various control locations and with the pilot in several attitudes, estimates of forces within the range normally encountered in flight were made to gain an indication of the accuracy of estimating control forces. The maximum aileron forces measured were of the order of 90 pounds, maximum elevator 200 pounds, and maximum rudder 450 pounds. The average forces applied with the controls in the neutral position for the various cockpit attitudes were of the order of 35, 95, and 400 pounds, respectively, for the ailerons, elevators, and rudder.
    Materialart: NACA-TN-550
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  • 49
    Publikationsdatum: 2019-06-28
    Beschreibung: A general test was made in the N.A.C.A. tank of a 1/12-size model of the hull of the British Singapore IIC flying boat loaned by the Director of Research, British Air Ministry. The results are given in charts and are compared with the results of tests of a model of an American flying-boat hull, the Sikorsky S-40. The Singapore hull has a greater hump resistance but a much lower high-speed resistance than the S-40.
    Materialart: NACA-TN-580
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  • 50
    Publikationsdatum: 2019-06-28
    Beschreibung: Charts are presented for determining the performance of airplanes having variable-pitch propellers, the pitch of which is assumed to be adjusted to maintain constant speed for all rates of flight. The charts are based on the general performance equations developed by Oswald in reference 1, and are used in a similar manner. Examples applying the charts to airplanes having both supercharged and unsupercharged engines are included.
    Materialart: NACA-TN-579
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  • 51
    Publikationsdatum: 2019-06-28
    Beschreibung: Full-scale wind-tunnel and flight tests were made of a Fairchild 22 airplane equipped with a Fowler flap to determine the effect of the flap on the performance and control characteristics of the airplane. In the wind-tunnel tests of the airplane with the horizontal tail surfaces removed, the flap was found to increase the maximum lift coefficient from 1.27 to 2.41. In the flight test, the flap was found to decrease the minimum speed from 58.8 to 44.4 miles per hour. The required take-off run to attain an altitude of 50 feet was reduced from 935 feet to 700 feet by the use of the flap, the minimum distance being obtained with five-sixths full deflection. The landing run from a height of 50 feet was reduced one-third. The longitudinal and directional control was adversely affected by the flap, indicating that the design of the tail surfaces is more critical with a flapped than a plain wing.
    Materialart: NACA-TN-578
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  • 52
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The cost in mean effective pressure of generating air flow in the combustion chambers of single-cylinder compression-ignition engines was determined for the prechamber and the displaced-piston types of combustion chamber. For each type a wide range of air-flow quantities, speeds, and boost pressures was investigated. Supplementary tests were made to determine the effect of lubricating-oil temperature, cooling-water temperature, and compression ratio on the friction mean effective pressure of the single-cylinder test engine. Friction curves are included for two 9-cylinder, radial, compression-ignition aircraft engines. The results indicate that generating the optimum forced air flow increased the motoring losses approximately 5 pounds per square inch mean effective pressure regardless of chamber type or engine speed. With a given type of chamber, the rate of increase in friction mean effective pressure with engine speed is independent of the air-flow speed. The effect of boost pressure on the friction cannot be predicted because the friction was decreased, unchanged, or increased depending on the combustion-chamber type and design details. High compression ratio accounts for approximately 5 pounds per square inch mean effective pressure of the friction of these single-cylinder compression-ignition engines. The single-cylinder test engines used in this investigation had a much higher friction mean effective pressure than conventional aircraft engines or than the 9-cylinder, radial, compression-ignition engines tested so that performance should be compared on an indicated basis.
    Materialart: NACA-TN-577
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  • 53
    Publikationsdatum: 2019-06-28
    Beschreibung: A model of the hull of the Navy PB-1 flying boat was tested in the N.A.C.A. tank as part of a program intended to provide information regarding the water performance of hulls of flying boats of earlier design for which hydrodynamic data have heretofore been unavailable. Tests were made according to the general method over the range of practical loadings with the model both fixed in trim and free to trim. A free-to-trim test according to the specific method was also made for the design load and take-off speed corresponding to those of the full-scale flying boat. The resistance obtained from the fixed-trim test was found to be about the same as that of the model of the NC flying-boat hull, and greater at the hump but smaller at high speeds than that of a model of the Sikorsky S-40 flying-boat hull.
    Materialart: NACA-TN-576
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  • 54
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: A method of determining the moments of inertia of an airplane from design data pertaining to the weights and locations of the component parts is described. The computations required to ascertain the center-of-gravity position are incorporated with the calculations of moments of inertia. A complete set of data and calculations for a modern airplane is given to illustrate the procedure. From a comparison between calculated values and measured values it is believed that the moments of inertia can be estimated within 10 percent by the use of this method.
    Materialart: NACA-TN-575
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  • 55
    Publikationsdatum: 2019-06-28
    Beschreibung: Four models with longitudinal steps on the forebody were developed by modification of a model of a conventional hull and were tested in the National Advisory Committee for Aeronautics (NACA) tank. Models with longitudinal steps were found to have smaller resistance at high speed and greater resistance at low speed than the parent model that had the same afterbody but a conventional V-section forebody. The models with a single longitudinal step had better performance at hump speed and as low high-speed resistance except at very light loads. Spray strips at angles from 0 degrees to 45 degrees to the horizontal were fitted at the longitudinal steps and at the chine on one of the two step models having two longitudinal steps. The resistance and the height of the spray were less with each of the spray strips than without; the most favorable angle was found to lie between 15 degrees and 30 degrees.
    Materialart: NACA-TN-574
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  • 56
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Several improvements that have been made on commercially available carbon-monoxide indicators to make them more suitable for aircraft use are described. These improvements include an automatic flow regulator, which permits the use of a simplified instrument on aircraft where a source of suction is available, and a more reliable alarm attachment. A field method for testing instruments on standard samples of carbon monoxide is described. Performance data and instructions in operation and maintenance are given.
    Materialart: NACA-TN-573
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  • 57
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was made to obtain information on the minimum quantity of air and power required to cool conventional air cooled cylinders at various operating conditions when using a blower. The results of these tests show that the minimum power required for satisfactory cooling with an overall blower efficiency of 100 percent varied from 2 to 6 percent of the engine power depending on the operating conditions. The shape of the jacket had a large effect on the cylinder temperatures. Increasing the air speed over the front of the cylinder by keeping the greater part of the circumference of the cylinder covered by the jacket reduced the temperatures over the entire cylinder.
    Materialart: NACA-TN-572
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  • 58
    Publikationsdatum: 2019-06-28
    Beschreibung: An empirical method is given for estimating the aerodynamic effect of ordinary and split flaps on airfoils similar to the Clark Y. The method is based on a series of charts that have been derived from an analysis of existing wind-tunnel data. Factors are included by which such variables as flap location, flap span, wing aspect ratio, and wing taper may be taken into account. A series of comparisons indicate that the method would be suitable for use in making preliminary performance calculations and in structural design.
    Materialart: NACA-TN-571
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  • 59
    Publikationsdatum: 2019-06-28
    Beschreibung: A series of tests was made in the N.A.C.A. free spinning tunnel to find the effect upon spinning characteristics of systematic changes in tail arrangement. The tests were made with a 1/16-scale made of a low-wing monoplane of modern design. The changes consisted of: (1) variation of the fuselage length; (2) variation of the fore-and-aft location of the vertical surfaces; and (3) variation of the vertical location of the horizontal surfaces. The spinning characteristics of the model, including the number of turns required for recovery, were found to vary systematically and regularly with systematic changes in the tail arrangement. The following changes in tail arrangement had harmful effects upon the recovery characteristics (which originally were excellent): (1) shortening the fuselage; (2) placing the vertical surfaces directly above the horizontal surfaces as compared with locations either fore or aft of this position; (3) moving the horizontal surfaces downward from their original location at the top of the fuselage.
    Materialart: NACA-TN-570
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  • 60
    Publikationsdatum: 2019-06-28
    Beschreibung: Performance tests were made using a rectangular displacer arranged so that the combustion air was forced through equal passages at either end of the displacer into the vertical-disk combustion chamber of a single-cylinder, four-stroke-cycle compression-ignition test engine. After making tests to determine optimum displacer height, shape, and fuel-spray arrangement, engine-performance tests were made at 1,500 and 2,000 r.p.m. for a range of boost pressures from 0 to 20 inches of mercury and for maximum cylinder pressures up to 1,150 pounds per square inch. The engine operation for boosted conditions was very smooth, there being no combustion shock even at the highest maximum cylinder pressures. Indicated mean effective pressures of 240 pounds per square inch for fuel consumptions of 0.39 pound per horsepower-hour have been readily reproduced during routine testing at 2,000 r.p.m. at a boost pressure of 20 inches of mercury.
    Materialart: NACA-TN-569
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  • 61
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: In order to determine whether or not flaps could be expected to have any beneficial effect on take-off performance, the distances required to take off and climb to an altitude of 50 feet were calculated for hypothetical airplanes, corresponding to relatively high-speed types and equipped with several types of flap. The types considered are the Fowler wing, the Hall wing, the split flap, the balanced split flap, the plain flap, and the external-airfoil flap. The results indicate that substantial reductions in take-off distance are possible through the use of flaps, provided that the proper flap angle corresponding to a given set of conditions is used. The best flap angle for taking off varies inversely as power loading and, to a much smaller extent, varies inversely with wing loading. Apparently, the best take-off characteristics are provided by the type of device in which the flap forms an extension to the main wing as in the case of the Fowler wing and the external-airfoil flap.
    Materialart: NACA-TN-568
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  • 62
    Publikationsdatum: 2019-06-28
    Beschreibung: The results of tests of six airfoils having the N.A.C.A. 230 mean line and varying in thickness from 0.06c to 0.21c are presented. These results agree with previous findings in showing that aerodynamically the best section is one of moderate thickness. The data are of value mainly in connection with the design of tapered wings having sections based on the N.A.C.A. 230 mean line.
    Materialart: NACA-TN-567
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  • 63
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: A 1/7.06 full-size model of the NC-type hull was tested in the N.A.C.A. tank by both the general method and the specific or free-to-trim method. The results of the tests are given in curves plotted as non dimensional coefficients and are compared with the test results of N.A.C.A. model 11-A. The NC model (N.A.C.A. model 44) shows higher resistance than model 11-A at hump speed but lower resistance at high speeds. Model 44 has a higher best trim angle at the jump and a lower maximum positive trimming moment than model 11-A. At high speeds the best trim angle and the trimming moments of the two models are approximately the same.
    Materialart: NACA-TN-566
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  • 64
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The procedure for obtaining air-speed and rate-of-climb measurements in performance tests of airships is described. Two methods of obtaining speed measurements, one by means of instruments in the airship and the other by flight over a measured ground course, are explained. Instruments, their calibrations, necessary correction factors, observations, and calculations are detailed for each method, and also for the rate-of-climb tests. A method of correction for the effect on density of moist air and a description of other methods of speed course testing are appended.
    Materialart: NACA-TN-564
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  • 65
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Large models of the Mark V and Mark VI floats used for single float seaplanes (National Advisory Committee for Aeronautics (NACA) models 41-A and 41-B, respectively) were tested in the NACA tank to provide general test data for typical single floats and a basis for possible improvements of their form. The resistance of model 41-B was greater than that of model 41-A, either when free to trim or at the best trim angle for each. The resistance of model 35-B (a pointed step hull tested free to trim) was less than either of the models at the hump speed, greater at intermediate planing speeds, and less at the speeds and loads near get-away, although the spray was generally worse owing to the absence of transverse flare. The results of the fixed-trim tests of model 41-A were cross plotted to obtain data at the angle for zero trimming moment and at the best trim angle. The trims assumed by models 41-A and 41-B, when tested free to trim, were found to be excessive at the hump speed. The corresponding trim of model 35-B was found to be approximately 3 degrees lower because of the lower angle of afterbody keel used in this model, and the maximum hump resistance was 15 percent lower.
    Materialart: NACA-TN-563
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  • 66
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The definitions of flexural center, torsional center, elastic center, and elastic axis are discussed. The calculation of elastic centers is dealt with in principle and a suggestion is made for the design of shear webs.
    Materialart: NACA-TN-562
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  • 67
    Publikationsdatum: 2019-06-28
    Beschreibung: Surveys of the air flow over the upper surface of four different airfoils were made in the full-scale wind tunnel to determine a satisfactory location for a fixed Pitot-static tube on a low-wing monoplane. The selection was based on small interference errors, less than 5 percent, and on a consideration of structural and ground handling problems. The most satisfactory location on the airfoils without flaps that were investigated was 10 percent of the chord aft and 25 percent of the chord above the trailing edge of a section approximately 40 percent of the semispan inboard of the wing tip. No satisfactory location was found near the wing when the flaps were deflected.
    Materialart: NACA-TN-561
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  • 68
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The sodium line-reversal method has been used in some preliminary measurements of flame temperature. Improvements in the method involving a photographic recorder and a means of correcting for the dirtiness of the windows are described. The temperatures so obtained are compared with those calculated from pressure diagrams.
    Materialart: NACA-TN-559
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  • 69
    Publikationsdatum: 2019-06-28
    Beschreibung: In the selection of materials for aircraft application, it is not enough to make the selection on a strength-weight basis alone. A strength-weight comparison is significant but other factors must be considered, for while a material with a high ratio of strength to weight may be perfectly satisfactory for one use, it may be totally unfitted for another. It is essential, among other things, that the probable nature, magnitude, and direction of the principal stresses be given special consideration. The following analysis has therefore been made with this in mind. An attempt has been made to cover insofar as possible the major, but not all the points, that a designer would consider in the use of "18-8", as it is commonly referred to, and 24ST aluminum alloy, as applied to aircraft. 24ST was selected for this comparison as it has practically replaced 17ST for aircraft construction and it appears to have the best combination of properties of the alloys now available for this purpose. The cost of fabrication has not been considered.
    Materialart: NACA-TN-560
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  • 70
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents a survey of previous theoretical and experimental investigations on wing flutter covering thirteen cases of flutter observed on airplanes. The direct cause of flutter is, in the majority of cases, attributable to (mass-) unbalanced ailerons. Under the conservative assumption that the flutter with the phase angle most favorable for excitation occurs only in two degrees of freedom, the lowest critical speed can be estimated from the data obtained on the oscillation bench. Corrective measures for increasing the critical speed and for definite avoidance of wing flutter, are discussed.
    Materialart: NACA-TM-782
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  • 71
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The available literature on rotating propeller oscillations reveals a lack of uniformity in interpretation, particularly as concerns the data on the overtone frequency with respect to the centrifugal forces. The present report is a survey of the existing data for computing the bending frequency and a check on the dependability of the calculating methods.
    Materialart: NACA-TM-783
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  • 72
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: Following an abstract of the well-known theory of torsion in compression, the writers give directions for the practical calculation of the values of C(sub BT) (resistance to flexure and torsion) and i(sub SP(exp 2)), which determine the torsion. The second part treats the experiments in support of the theory of torsion of plain and flanged angle sections.
    Materialart: NACA-TM-784
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  • 73
    facet.materialart.
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
    Materialart: NACA-TM-788
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  • 74
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The present paper describes the results of a stability investigation on symmetrical velocity profiles in a channel and of boundary-layer profiles. The effect of friction was assumed to be vanishing and did not occur in the stability consideration so far as it had been resorted to for preparatory asymptotic considerations. Proceeding on very general premises as regards the form of the velocity distribution, a proof was deduced of the elementary theorem that velocity profiles with inflection points are unstable.
    Materialart: NACA-TM-792
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  • 75
    facet.materialart.
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: After a brief discussion of the work done up to now on an unwarped wing of constant chord spanning a free jet, the computation of the circulation and lift distribution for different forms of warped wings spanning rectangular and circular jets was carried out. The computed values are compared with test values and the agreement is found to be good. The effect of placing the wing eccentrically is slight and may be applied as a correction factor to the data obtained for wing placed in middle of jet.
    Materialart: NACA-TM-796
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  • 76
    facet.materialart.
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This report analyzes the heating and vaporization process of fuel droplets in a compression-ignition engine on the basis of the theory of similitude - according to which, the period for heating and complete vaporization of the average size fuel drop is only a fraction of the actually observed ignition lag. The result is that ignition takes place in the fuel vapor air mixture rather than on the surface of the drop. The theoretical result is in accord with the experimental observations by Rothrock and Waldron. The combustion shock occurring at lower terminal compression temperature, especially in the combustion of coal-tar oil, is attributable to a simultaneous igniting of a larger fuel-vapor volume formed prior to ignition.
    Materialart: NACA-TM-797
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  • 77
    Publikationsdatum: 2019-06-28
    Beschreibung: Determination of the spontaneous oscillations of a wing or tail unit entail many difficulties, both the mathematical determination and the determination by static wing oscillation tests being far from successful and flight tests involving very great risks. The present paper gives a method developed at the Junkers Airplane Company by which the critical velocity with respect to spontaneous oscillations of increasing amplitude can be ascertained in flight tests without undue risks, the oscillation of the surface being obtained in the tests by the application of an external force.
    Materialart: NACA-TM-806
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  • 78
    facet.materialart.
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    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: In this paper is a discussion of the general principles for open sections of any shape. In what follows the torsion will be computed and on the basis of the results it will be possible to obtain a proper design of section in each case. The torsion of buckling members for the case where they are centrally loaded, leads to a problem in pure stability and is similar to that of stressed beams.
    Materialart: NACA-TM-807
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  • 79
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This adaptation of a Russian report reveals the effect of maximum cross section of an engine as well as the interest attaching to a choice not solely based on horsepower. The tabulation gives a comparison between different engines restored at 5,000 meters. Radial versus inverted in-line engines are also compared.
    Materialart: NACA-TM-812
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 80
    Publikationsdatum: 2019-06-28
    Beschreibung: This investigation is a detailed description of the soap-bubble, or constant-pressure, method as applied to the explosive oxidation of carbon monoxide.
    Materialart: NACA-TR-532
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 81
    Publikationsdatum: 2019-06-28
    Beschreibung: A flight investigation of the spinning of the F4B-2 single-seat fighter airplane was made for the purpose of finding modifications that would eliminate dangerous spin tendencies exhibited by this type of airplane in service. The effects on steady spins and on recoveries of changing the loading, enlarging the fin areas, changing the elevator plan form, and raising the horizontal surfaces, were determined.
    Materialart: NACA-TR-529
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 82
    Publikationsdatum: 2019-06-28
    Beschreibung: A family of related airfoils having the position of maximum camber unusually far forward was investigated in the variable-density tunnel as an extension of the study recently completed of a large number of related airfoils. The new airfoils gave improved characteristics over those previously investigated, especially in regard to the pitching moment. Some of the new sections are markedly superior to well-known and commonly used sections and should replace them in applications requiring a slightly cambered section of moderate thickness having a small pitching-moment coefficient.
    Materialart: NACA-TR-537
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 83
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was made to determine whether a sufficient amount of hydrogen could be efficiently burned in a compression-ignition engine to compensate for the increase of lift of an airship due to the consumption of the fuel oil. The performance of a single-cylinder four-stroke-cycle compression-ignition engine operating on fuel oil alone was compared with its performance when various quantities of hydrogen were inducted with the inlet air. Engine-performance data, indicator cards, and exhaust-gas samples were obtained for each change in engine-operating conditions.
    Materialart: NACA-TR-535
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 84
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation to study the effect of water vapor upon the spatial speed of flame in equivalent mixtures of carbon monoxide and oxygen at various total pressures from 100 to 780 mm.hg. These results show that, within this pressure range, an increase in flame speed is produced by increasing the mole fraction of water vapor at least as far as saturation at 25 degrees c., and that the rate of this increase is greater the higher the pressure. It is evident that water vapor plays an important part in the explosive oxidation of carbon monoxide; the need for further experimental evidence as to the nature of its action is indicated.
    Materialart: NACA-TR-531
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 85
    Publikationsdatum: 2019-06-28
    Beschreibung: Flight tests were made on PCA-2 autogiro with wing settings of 2.2 degrees, 0.9 degrees, and -0.5 degrees. The wing load and rotor speed were measured in steady glides. The results obtained show that a wide variation in rotor speed as a function of air speed can be obtained by a suitable adjustment of the wing setting; that by decreasing the wing setting the upper safe flying speed, determined by the decrease is rotor speed, is greatly increased; and that the interference of the wing on the rotor thrust and lift coefficients is negligible.
    Materialart: NACA-TR-523
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 86
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents a discussion of longitudinal stability in gliding flight together with a series of charts with which the stability characteristics of any airplane may be readily estimated.
    Materialart: NACA-TR-521
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 87
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the tests results of a series of tests made of the sprays from 14 fuel injection nozzles of 9 different types, the sprays being injected into air at atmospheric density and at 6 and 14 times atmospheric density. High-speed spark photographs of the sprays from each nozzle at each air density were taken at the rate of 2,000 per second, and from them were obtained the dimensions of the sprays and the rates of spray-tip penetration. The sprays were also injected against plasticine targets placed at different distances from the nozzles, and the impressions made in the plasticine were used as an indication of the distribution of the fuel within the spray. Cross-sectional sketches of the different types of sprays are given showing the relative sizes of the spray cores and envelopes. The characteristics of the sprays are compared and discussed with respect to their application to various types of engines.
    Materialart: NACA-TR-520
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 88
    Publikationsdatum: 2019-06-28
    Beschreibung: A series of wind tunnel tests of a rectangular Clark Y wing was made with the NACA spinning balance as part of a general program of research on airplane spinning. All six components of the aerodynamic force and moment were measured throughout the range of angles of attack, angles of sideslip, and values omega b/2v likely to be attained by a spinning airplane; the results were reduced to coefficient form. It is concluded that a conventional monoplane with a rectangular Clark y wing can be made to attain spinning equilibrium throughout a wide range of angles of attack but that provision of a yawing moment coefficient of -0.02 (against the spin) by the tail, fuselage, and interferences will insure against attainment of equilibrium in a steady spin.
    Materialart: NACA-TR-519
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 89
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of flight tests made on five different lateral control devices that appeared adaptable to wings fitted with full span flaps: controllable auxiliary airfoils (airfoils mounted above and forward of the leading edge of the wings), external ailerons (airfoils mounted above the wing and slightly forward of its maximum ordinate), upper-surface ailerons (similar to split trailing-edge flaps except that they constitute the upper surface of the wing), ailerons that retract into the wing when in neutral, and narrow-chord conventional ailerons in combination with a special type of split flap that retracts into the under surface of the wing forward of the ailerons. The devices were tested on a small parasol monoplane. Experienced gained in the use of flaps during these tests has indicated the desirability of a flap that can be operated quickly and easily.
    Materialart: NACA-TR-517
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 90
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation to determine the effect of baffles on the temperature distribution and the heat-transfer coefficient of finned cylinders. The tests were conducted in a 30-inch wind tunnel on electrically heated cylinders with fins of 0.25 and 0.31 inch pitch. The results of these tests showed that the use of integral baffles gave a reduction of 31.9 percent in the rear wall temperatures and an increase of 54.2 percent in the heat transfer coefficient as compared with a cylinder without baffles.
    Materialart: NACA-TR-511
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 91
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of wind-tunnel tests on a model gyroplane rotor 10 feet in diameter. The rotor blades had zero sweepback and zero offset; the hub contained a feathering mechanism that provided control of the rotor rolling moment, but not of the pitching moment. The rotor was tested with 4 blades and with 2 blades. The entire useful range of pitch settings and tip-speed ratios was investigated including the phase of operation in which the rotor turned very slowly, or idled.
    Materialart: NACA-TR-536
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 92
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of performance test conducted on a six-cylinder commercial fuel-injection pump that was adjusted to give uniform fuel distribution among the cylinders at a throttle setting of 0.00038 pound per injection and a pump speed of 750 revolutions per minute. The throttle setting and pump speed were then varied through the operating range to determine the uniformity of distribution and regularity of injection.
    Materialart: NACA-TR-533
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 93
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation conducted in the NACA 7 by 10-foot wind tunnel of control surfaces equipped with tabs for reducing the control forces or trimming the aircraft. Two sizes of ordinary ailerons with several sizes of attached and inset tabs were tested on a Clark y wing. Tabs were also tested in combination with auxiliary balances of the horn and paddle types, and with a frise balance aileron. A tail-surface model of symmetrical section, equipped with tabs, was tested with 40 percent of the area movable (elevator) when used as a horizontal tail and 60 percent of the area movable (rudder) when used as a vertical tail. The half-span tail-surface model was tested with and without a reflection plane. The results of the tests indicated that inset tabs were superior to attached tabs for the same ratio of tab/control surface deflection.
    Materialart: NACA-TR-528
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 94
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The speed distribution in a laminar boundary layer on the surface of an elliptic cylinder, of major and minor axes 11.78 and 3.98 inches, respectively, has been determined by means of a hot-wire anemometer. The direction of the impinging air stream was parallel to the major axis. Special attention was given to the region of separation and to the exact location of the point of separation. An approximate method, developed by K. Pohlhausen for computing the speed distribution, the thickness of the layer, and the point of separation, is described in detail; and speed-distribution curves calculated by this method are presented for comparison with experiment.
    Materialart: NACA-TR-527
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 95
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: This report describes a method of determining the turbulence in wind tunnels. The effect of turbulence upon the diffusion of heat from a small electrically heated wire in an air stream was investigated. The turbulence of the stream was introduced by a series of geometrically similar screens placed one at a time across the upstream section of the tunnel. With the wire set at various distances from the screens, curves of temperature distribution were obtained by traversing the heated wake at a distance of 2 inches behind the wire with a small thermocouple.
    Materialart: NACA-TR-524
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 96
    Publikationsdatum: 2019-06-28
    Beschreibung: This report is a compilation of previously published articles on formulas and methods of calculation for the determination of the strength and stability of plate and shell construction as employed in airplane design. In particular, it treats the problem of isotropic, orthotopic, and stiffened rectangular plates, thin curved panels, and circular cylinders under various loading conditions. The purpose of appending the pertinent literature references following the subjects discussed was to facilitate a comprehensive study of the treated problems.
    Materialart: NACA-TM-785
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 97
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: For floats and hulls having V bottoms the impact force does not necessarily increase with increasing width. Therefore, the weight of the float landing gear, side walls, and other parts, and of the fuselage construction need not be increased with increasing bottom width, but the weight of the bottom construction itself, on the other hand, does not increase with increase in bottom width and is largely determined by the type of construction.
    Materialart: NACA-TM-811
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 98
    Publikationsdatum: 2019-06-28
    Beschreibung: In the present report a comparison is made between the scale obtained with mixtures of cetane and l-methyl naphthalene in a bomb, and that obtained with the same fuels in a Waukesha engine. The tests were conducted in a metal bomb heated by a Nichrome spiral. The fuel was injected into the bomb from a Bosch jet by means of a specially constructed plunger pump. The instant injection and the pressure curve in the bomb were registered by a beam of light which was reflected from a mirror connected to the needle of the jet and to a membrane indicator.
    Materialart: NACA-TM-813
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 99
    Publikationsdatum: 2019-06-28
    Beschreibung: The present experiments treat the stress of actual tension fields within the elastic range. They give the magnitude of the flexural stresses due to wrinkling. They also disclose, particularly by slightly exceeded buckling load, the marked unloading - as compared with the tension-field theory - of the uprights as a result of the flexural stiffness of the web plate. The test sheets were clamped at the edges and brought to buckling through shearing and compressive stresses applied in the direction of the long sides.
    Materialart: NACA-TM-809
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 100
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-28
    Beschreibung: The object of the present experiments is a more exact determination of the effective width for the case of pure compression and of the sheet clamped at the angle section. From the experimental data of the effective width the calculation of the buckling load of an angle joined to a thin sheet is then deduced. The test material consisted of spring-hardened brass sheet.
    Materialart: NACA-TM-814
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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