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  • 1980-1984  (4)
  • 1981  (4)
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  • 1980-1984  (4)
Year
  • 1
    Electronic Resource
    Electronic Resource
    Polyfunctional zeolite catalysts in the benzene-olefin-hydrogen system (1981)
    Springer
    Reaction kinetics and catalysis letters 17 (1981), S. 385-389 
    Details
    ISSN: 1588-2837
    Source: Springer Online Journal Archives 1860-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Abstract Исследована реакция алкилирования бензола олефинами C2−C4 в присутствии водорода на подвергнутом термопаровой обработке цеолитном катализаторе, содержащем катионы лантана и никеля. Обнаружено промотирующее действие водорода на протекание реакции алкилирования бензола пропиленом.
    Notes: Abstract Benzene alkylation by C2−C4 olefins in the presence of hydrogen over a steam-treated zeolite catalyst containing lanthanum and nickel, has been studied. The promoting action of hydrogen on benzene alkylation by propylene has been established.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF02065851
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Unknown
    A vortex-lattice method for calculating longitudinal dynamic stability derivatives of oscillating delta wings (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A nonsteady vortex-lattice method is introduced for predicting the dynamic stability derivatives of a delta wing undergoing an oscillatory motion. The analysis is applied to several types of small oscillations in pitch. The angle of attack varied between + or - 1 deg, with the mean held at 0 deg when the flow was assumed to be attached and between + or - 1 deg and the mean held at 15 deg when both leading-edge separation and wake roll-up were included. The computed results for damping in pitch are compared with several other methods and with experiments, and are found to be consistent and in good agreement.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 81-1876 , Atmospheric Flight Mechanics Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    A vortex-lattice method for calculating lifting-surface interference (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The interference effect of closely coupled lifting surfaces was investigated. A nonsteady vortex-lattice method was applied to calculate the steady-state and nonsteady lift characteristics of configurations having interference effects. The configurations consist of low-aspect-ratio delta wings, at low and high angles of attack. Leading-edge separation and wake roll-up are simulated by a time-dependent wake-shedding procedure. For steady-state flow conditions, this numerical procedure saves a considerable amount of computer time, compared with iterative methods, and yields the same results. A better understanding of the interference effect can be gained by using the method to study the transient behavior. The nonsteady approach also offers the capability of calculating various nonsteady motions, as is demonstrated in the calculation of the longitudinal damping.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1662 , Aircraft Systems and Technology Conference; Aug 11, 1981 - Aug 13, 1981; Dayton, OH
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Wind-tunnel measurements of wing-canard interference and a comparison with various theories (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Wind-tunnel tests and analyses of the aerodynamics of wing-canard combinations for low speed applications are presented. Systematic tests are conducted in a 7 x 10 wind tunnel to explore various combinations of wing-canard vertical and horizontal positioning. The goals of the tests are (1) to investigate potential improved stalling characteristics over conventional tail-aft configurations, (2) to investigate the existence of a lift coefficient advantage, and (3) to determine induced drag levels. The measurements obtained are compared with calculations made using the Prandtl-Munk theory, and with a vortex-lattice panel code. Results indicate that the panel code gives excellent results for lift and induced drag at moderate lift coefficient, whereas Prandtl-Munk theory gives conservative results for induced drag. The application is a light transport aircraft used for short-haul operations.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 810575 , Business Aircraft Meeting and Exposition; Apr 07, 1981 - Apr 10, 1981; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
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