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  • 1
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    Unknown
    In:  Other Sources
    Publication Date: 2011-08-11
    Description: Terminal facilities, support equipment and operational characteristics of V/STOL aircraft
    Keywords: AIRCRAFT
    Format: text
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  • 2
    Publication Date: 2018-06-05
    Description: Experience has shown that the determination of the take-off and. landing characteristics of airplanes requires specialized, equipment of a high degree of precision and reliability and demands great care in the evaluation and interpretation of data. It is believed, therefore, that a description of the apparatus and methods that have been developed by the NACA for these measurements might be of considerable interest, particularly to flight-test groups that have had little experience with landing and. take-off measurements. The basic principles and essential details of the Committee's equipment are described, the methods of utilizing the apparatus and of reducing the data are explained, and sample test results are presented.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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  • 3
    Publication Date: 2019-05-11
    Description: Aircraft vortex wakes in relation to terminal operations and traffic control
    Keywords: NUCLEAR ENGINEERING
    Type: NASA-TN-D-1777
    Format: application/pdf
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  • 4
    Publication Date: 2019-05-21
    Description: Safety hazard of aircraft vortex wakes and precautions in airport terminal control
    Keywords: ELECTRONICS
    Type: NASA-TM-X-51683
    Format: application/pdf
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  • 5
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 3-13
    Format: application/pdf
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  • 6
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    Unknown
    In:  Other Sources
    Publication Date: 2019-05-22
    Keywords: unknown
    Type: NASA-TM-X-51700
    Format: text
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  • 7
    Publication Date: 2019-06-28
    Type: NACA-RM-L8A28d
    Format: application/pdf
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  • 8
    Publication Date: 2019-06-28
    Description: This report presents the results of test made to determine the rolling friction of airplane wheels and tires under various conditions of wheel loading, tire inflation pressure, and ground surface. The effect of wheel-bearing type was also investigated. Six pairs of wheels and tires were tested including two sizes of each of the types designated as standard (high pressure), low pressure, and extra low pressure. The results of calculations intended to show the effect of variations in rolling friction on take-off are also presented.
    Type: NACA-TR-583
    Format: application/pdf
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  • 9
    Publication Date: 2019-06-28
    Description: A flight investigation was conducted to determine the lateral-control characteristics of retractable ailerons installed on a highly tapered wing. The effectiveness of the ailerons in producing roll was measured at various air speeds with full-span plain flaps both neutral and deflected 45 degrees. The direction of the yawing moment created by the ailerons was also noted. The lateral control provided by the retractable ailerons used in this investigation was approximately the same as that obtained with the plain ailerons of equal span with which the airplane was previously equipped. The amount of control available was found to be somewhat inadequate, apparently because of the rather short span of the ailerons (0.327 of the wing span). It is likely that, with an aileron span of from 0.50 to 0.60 of the wing span, a satisfactory degree of control would be obtained. With the full-span flaps deflected 45 degrees, the rolling action of the ailerons was increased about 30 percent over that obtained with the flaps neutral at the same speed. The yawing moment produced by the ailerons was in the same sense as the rolling moment, i.e., right roll was accompanied by yaw. Lag in the response of the rolling action to control application was not large enough to be noticed by the pilots. No appreciable control force was apparent to the pilots, which was considered somewhat undesirable. Minor modifications in the design of the ailerons, however, would probably correct this fault.
    Type: NACA-TN-714
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-28
    Description: This paper presents the results of flight tests made to determine the effect of slots and flaps on the lateral control of a low-wing monoplane. Maximum angular accelerations in roll and yaw produced by sudden application of the ailerons and maximum accelerations in yaw produced by sudden application of the rudder during gliding flight were recorded for the following wing arrangements: (a) no auxiliary device; (b) full-span slots; (c) plain flaps; (d) flaps and full-span slots; (e) wing-tip slots. Rolling- and yawing-moment coefficients were derived from the accelerations. The full span slots and the flaps each had about the same influence on the aileron rolling moments. At values of the lift coefficient obtainable with the plain wing, the effect of these devices was negligible. At the higher lift coefficients obtainable with these devices, the rolling-moment coefficients increased slightly but, despite this increase, the aileron effectiveness progressively decreased with increasing lift coefficient, owing to the corresponding reduction in air speed. In the range covered by the tests, the effectiveness of the controls was appreciably reduced by the wing-tip slots. The adverse yawing moment of the ailerons experienced at the large lift coefficients obtained with the flaps was appreciably less than at similar lift coefficients obtained with either full-span or wing-tip slots. The yawing moments produced by the rudder were only slightly affected by the use of the auxiliary devices. The airplane was found to be laterally unstable with all combinations tested. Because of the angular velocities acquired in the time taken to deflect the ailerons the rolling moments recorded in flight were only about two thirds the values that would have been obtained with the wing restrained as in wind-tunnel tests.
    Type: NACA-TN-478
    Format: application/pdf
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