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  • Other Sources  (6)
  • Aircraft Design, Testing and Performance  (3)
  • Aircraft Propulsion and Power  (2)
  • 1936  (1)
  • 2000-2004
  • 1950-1954
  • 1935-1939  (6)
  • 1937  (6)
Collection
  • Other Sources  (6)
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  • 2000-2004
  • 1950-1954
  • 1935-1939  (6)
Year
  • 1
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    Witterung und Pflanzenwachstum im Jahre 1936 unter besonderer Berücksichtigung Bayerns (1937)
    In:  Prakt. Blätt. Pflanzenb. u. –schutz 14;p. 343-348
    Details
    Publication Date: 1937
    Description: Der Autor schildert detailliert den Witterungsverlauf des Vegetationsjahres 1935/36, gibt eine kleine Übersicht über die aufgetretenen Pflanzenkarankheiten und -schädlinge und bringt beides ansatzweise in einen Zusammenhang. Zudem listet er die Erträge des Vegetationsjahres auf und beurteilt diese. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bayern ; 1936 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Wachstum ; Witterung ; Hackfrüchte ; Hochwasser
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    BIBLIOGRAPHY INKA BB
  • 2
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    Notes on Factors Affecting Geometrical Arrangement of Tricycle-Type Landing Gear (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The effects of the geometrical arrangement of tricycle landing gears on various characteristics of an airplane equipped with such landing gear is discussed. The characteristics discussed include directional stability, overturning tendencies, steering and ground handling, shimmy, takeoff, and porpoising. The conclusions are summarized in a table.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-63
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The Transition Phase in the Take-Off of an Airplane, Special Report (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was undertaken to determine the character and importance of the transition phase between the ground run and steady climb in the takeoff of an airplane and the effects of various factors on this phase and on the airborne part of the takeoff as a whole. The information was obtained from a series of step-by-step integrations, which defined the motion of the airplane during the transition and which were based on data derived from actual takeoff tests of a Verville AT airplane. Both normal and zoom takeoffs under several loading and takeoff speed conditions were considered. The effects of a moderate wind with a corresponding wind gradient and the effect of proximity of the ground were also investigated. The results show that, for normal takeoffs, the best transition was realized at the lowest possible takeoff speed. Moreover, this speed gave the shortest overall takeoff distance for normal takeoffs. Zoom takeoffs required a shorter overall takeoff run than normal takeoffs, particularly with a heavy landing, if the obstacle to be cleared was sufficiently high (greater than 50 feet); no advantage was indicated to the airplane with a light loading if the height to be cleared was less. The error resulting from the neglect of the transition in the calculation of the airborne distance of takeoff was found to vary from 4% with the heaviest loading considered to -4% with the lightest loading for normal takeoffs over a 100-ft obstacle; the percentage error was twice as great for a 50-foot obstacle. For zoom takeoffs the error attained much greater values. The average wind gradient corresponding to a 5-mile-per-hour surface wind reduced the airborne distance required to clear a 50-foot obstacle by about 9% with the lightest loading and 16% with the heaviest loading; for both cases. The overall reduction due to this wind was approximately twice that resulting from the wind gradient alone. A simple expression for the reduction of observed takeoff performance to no-wind conditions is presented. Ground effect is shown to reduce the airborne distance to attain a height of 50 foot by 10% with the lightest loading and 16% with the heaviest loading; for a 100-foot obstacle the percentage reduction was about 1/2 as great.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-70
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model, Special Report (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: In the design of a cowling a certain pressure drop across the cylinders of a radial air-cooled engine is made available. Baffles are designed to make use of this available pressure drop for cooling. The problem of cooling an air-cooled engine cylinder has been treated, for the most part, from considerations of a large heat-transfer coefficient. The knowledge of the precise cylinder characteristics that give a maximum heat-transfer coefficient should be the first consideration. The next problem is to distribute this ability to cool so that the cylinder cools uniformly. This report takes up the problem of the design of a baffle for a model cylinder. A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that the cooling can be improved 20% by using a correctly designed baffle. Such a gain is as effective in cooling the cylinder with the improved baffle as a 65% increase in pressure drop across the standard baffle and fin tips.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-64
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Stability of Castering Wheels for Aircraft Landing Gears, Special Report (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: In many installations of castering rubber-tired wheels there is a tendency for the wheel to oscillate violently about the spindle axis. This phenomenon, popularly called 'shimmy,' has occurred in some airplane tail wheels and has been corrected in two ways: first by the application of friction in the spindles of the tail wheels; and, second, by locking the wheels while taxiing at high speeds. Shimmy is common with the large wheels used as nose wheels in tricycle landing gears and, since it is impossible to lock the wheels, friction in the nose-wheel spindle has been the sole means of correction. Because the nose wheel is larger than the conventional tail wheel and usually carries a greater load, the larger amounts of spindle friction necessary to prevent shimmy are objectionable. the present paper presents a theoretical and experimental study of the problem of the stability of castering wheels for airplane landing gears. On the basis of simplified assumptions induced from experimental observations, a theoretical study has been made of the shimmy of castering wheels. The theory is based on the discovery of a phenomenon called 'kinematic shimmy' and is compared quantitatively with the results of model experiments. Experimental checks, using a model having low-pressure tires, are reported and the applicability of the results to full scale is discussed. Theoretical methods of estimating the spindle viscous damping and spindle solid friction necessary to avoid shimmy - lateral freedom - is introduced.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-67
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Tandem Air Propellers (1937)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Tests of 2-blade, adjustable-pitch, counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency, were made at Stanford University. The characteristics, for 15 degrees, 25 degrees, 35 degrees, and 45 degrees pitch settings at 0.75 R of the forward propeller and for 8 1/2%, 15% and 30% diameter spacings, were compared with those of 2-blade and 4-blade propellers of the same blade form. The tests showed that the efficiency of the tandem propellers was from 0.5% to 4% greater than that of a 4-blade propeller and, at the high pitch settings, not appreciable inferior to that of a 2-blade propeller. It was found that the rear tandem propeller should be set at a pitch angle slightly less than that of the forward propeller to realize the condition of equal power at maximum efficiency. Under this condition the total power absorbed by the tandem propellers was from 3% to 9% more than that absorbed by the 4-blade propeller and about twice that absorbed by a 2-blade propeller.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-66
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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