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  • Weitere Quellen  (41)
  • Aircraft Design, Testing and Performance
  • Aircraft Propulsion and Power
  • FACILITIES, RESEARCH, AND SUPPORT
  • Organic Chemistry
  • unknown
  • 2000-2004  (31)
  • 1955-1959  (10)
  • 1925-1929
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  • 1
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    Corrugated and Composite Nozzle-Inlets for Thrust and Noise Benefits (2004)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The following research results are based on development of an approach previously proposed and investigated in for optimum nozzle design to obtain maximum thrust. The design was denoted a Telescope nozzle. A Telescope nozzle contains one or several internal designs, which are inserted at certain locations into a divergent conical or planar main nozzle near its exit. Such a design provides additional thrust augmentation over 20% by comparison with the optimum single nozzle of equivalent lateral area, What is more, experimental acoustic tests have discovered an essential noise reduction due to application of Telescope nozzles. In this paper, some additional theoretical results are presented for Telescope nozzles and a similar approach is applied for aero-performance improvement of a supersonic inlet. Numerical simulations were conducted for supersonic flow into the divergent portion of a 2D or axisymmetric nozzle with several plane or conical designs as well as into a 2D or axisymmetric supersonic inlet with a forebody. The Kryko-Godunov marching numerical scheme for inviscid supersonic flows was used. Several cases were tested using the NASA CFL3d and IM/MSU Russian codes based on the full Navier-Stokes equations. Numerical simulations were conducted for non reacting flows (both codes) as well as for real high temperature gas flows with non-equilibrium chemical reactions (the latter code). In general, these simulations have confirmed essential benefits of Telescope design applications in propulsion system. Some preliminary numerical simulations of several typical inlet designs were conducted with the goal of inlet design optimization for maneuvering flight conditions.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: AIAA Paper 2001-1893 , AIAA/NAL-NASDA-ISAS 10th International Space Planes and Hypersonic Systems and Technologies Conference; Apr 24, 2001 - Apr 27, 2001; Kyoto; Japan
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 2
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    Intermittent Flow Regimes in a Transonic Fan Airfoil Cascade (2002)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A study was conducted in the NASA Glenn Research Center linear cascade on the intermittent flow on the suction surface of an airfoil section from the tip region of a modern low aspect ratio fan blade. Experimental results revealed that, at a large incidence angle, a range of transonic inlet Mach numbers exist where the leading-edge shock-wave pattern was unstable. Flush mounted high frequency response pressure transducers indicated large local jumps in the pressure in the leading edge area, which generates large intermittent loading on the blade leading edge. These measurements suggest that for an inlet Mach number between 0.9 and 1.0 the flow is bi-stable, randomly switching between subsonic and supersonic flows. Hence, it appears that the change in overall flow conditions in the transonic region is based on the frequency of switching between two stable flow states rather than on the continuous increase of the flow velocity. To date, this flow behavior has only been observed in a linear transonic cascade. Further research is necessary to confirm this phenomenon occurs in actual transonic fans and is not the byproduct of an endwall restricted linear cascade.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NASA/TM-2002-211375 , E-13199 , NAS 1.15:211375 , Ninth International Symposium on Transport Phenomena and Dynamics of Rotating Machinery; Feb 10, 2002 - Feb 14, 2002; Honolulu, HI; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 3
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    Preliminary studies of manned satellites. Winged configurations (1958)
    In:  CASI
    Details
    Publikationsdatum: 2005-01-20
    Schlagwort(e): unknown
    Materialart: NACA CONF. ON HIGH-SPEED AERODYN. 1958; P 45-57
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 4
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    ON MAGNETO-AERODYNAMIC BOUNDARY LAYERS (1957)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-17
    Schlagwort(e): FACILITIES, RESEARCH, AND SUPPORT
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 5
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    Engines (1957)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): unknown
    Materialart: NACA 1957 FLIGHT PROPULSION CONF. 1957; P 53-76
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 6
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    Probabilistic Life and Reliability Analysis of Model Gas Turbine Disk (2002)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: In 1939, W. Weibull developed what is now commonly known as the "Weibull Distribution Function" primarily to determine the cumulative strength distribution of small sample sizes of elemental fracture specimens. In 1947, G. Lundberg and A. Palmgren, using the Weibull Distribution Function developed a probabilistic lifing protocol for ball and roller bearings. In 1987, E. V. Zaretsky using the Weibull Distribution Function modified the Lundberg and Palmgren approach to life prediction. His method incorporates the results of coupon fatigue testing to compute the life of elemental stress volumes of a complex machine element to predict system life and reliability. This paper examines the Zaretsky method to determine the probabilistic life and reliability of a model gas turbine disk using experimental data from coupon specimens. The predicted results are compared to experimental disk endurance data.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: Fifth Annual Workshop on the Application of Probabilistic Methods for Gas Turbine Engines; 603-625; NASA/CP-2002-211682
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 7
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    Cryogenic Electric Motor Tested (2004)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-02
    Beschreibung: Technology for pollution-free "electric flight" is being evaluated in a number of NASA Glenn Research Center programs. One approach is to drive propulsive fans or propellers with electric motors powered by fuel cells running on hydrogen. For large transport aircraft, conventional electric motors are far too heavy to be feasible. However, since hydrogen fuel would almost surely be carried as liquid, a propulsive electric motor could be cooled to near liquid hydrogen temperature (-423 F) by using the fuel for cooling before it goes to the fuel cells. Motor windings could be either superconducting or high purity normal copper or aluminum. The electrical resistance of pure metals can drop to 1/100th or less of their room-temperature resistance at liquid hydrogen temperature. In either case, super or normal, much higher current density is possible in motor windings. This leads to more compact motors that are projected to produce 20 hp/lb or more in large sizes, in comparison to on the order of 2 hp/lb for large conventional motors. High power density is the major goal. To support cryogenic motor development, we have designed and built in-house a small motor (7-in. outside diameter) for operation in liquid nitrogen.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: Research and Technology 2003; NASA/TM-2004-212729
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 8
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    "Fan-Tip-Drive" High-Power-Density, Permanent Magnet Electric Motor and Test Rig Designed for a Nonpolluting Aircraft Propulsion Program (2004)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-05
    Beschreibung: A scaled blade-tip-drive test rig was designed at the NASA Glenn Research Center. The rig is a scaled version of a direct-current brushless motor that would be located in the shroud of a thrust fan. This geometry is very attractive since the allowable speed of the armature is approximately the speed of the blade tips (Mach 1 or 1100 ft/s). The magnetic pressure generated in the motor acts over a large area and, thus, produces a large force or torque. This large force multiplied by the large velocity results in a high-power-density motor.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: Research and Technology 2003; NASA/TM-2004-212729
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 9
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    Longitudinal aerodynamic characteristics of various configurations of a revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01 (1956)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Schlagwort(e): unknown
    Materialart: NACA-RM-SL56E07A
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 10
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    An airborne simulator investigation of the accuracy of an optical track command missile guidance system (1956)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Schlagwort(e): unknown
    Materialart: NACA-RM-A56G24
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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