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  • 1
    Electronic Resource
    Electronic Resource
    Record conditions for cycling (1994)
    [s.l.] : Nature Publishing Group
    Nature 371 (1994), S. 552-552 
    Details
    ISSN: 1476-4687
    Source: Nature Archives 1869 - 2009
    Topics: Biology , Chemistry and Pharmacology , Medicine , Natural Sciences in General , Physics
    Notes: [Auszug] SIR - Miguel Indurain recently broke the world 1-hour cycling record, riding 53.040 km. The previous record was held by Graeme Obree, who rode an innovative bicycle of his own design and manufac-ture. Subsequently, the UCI (Union Cyc-liste Internationale) changed its rules to outlaw such ...
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1038/371552d0
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    Paper (German National Licenses)
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  • 2
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    Human-Powered Flight (1985)
    Springer Nature
    Details
    Publication Date: 1985-11-01
    Print ISSN: 0036-8733
    Electronic ISSN: 1946-7087
    Topics: Biology , Natural Sciences in General , Physics
    Published by Springer Nature
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    PAPER CURRENT
  • 3
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    Screened expanding turning-vane concept (2020)
    Springer
    Details
    Publication Date: 2020-02-21
    Print ISSN: 0723-4864
    Electronic ISSN: 1432-1114
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 4
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    Record conditions for cycling (1994)
    Springer Nature
    Details
    Publication Date: 1994-10-01
    Print ISSN: 0028-0836
    Electronic ISSN: 1476-4687
    Topics: Biology , Chemistry and Pharmacology , Medicine , Natural Sciences in General , Physics
    Published by Springer Nature
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    PAPER CURRENT
  • 5
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    Advanced Configurations for Very Large Subsonic Transport Airplanes (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent aerospace industry interest in developing a subsonic commercial transport airplane with 50 percent greater passenger capacity than the largest existing aircraft in this category (the Boeing 747-400 with approximately 400-450 seats) has generated a range of proposals based largely on the configuration paradigm established nearly 50 years ago with the Boeing B-47 bomber. While this basic configuration paradigm has come to dominate subsonic commercial airplane development since the advent of the Boeing 707/Douglas DC-8 in the mid-1950's, its extrapolation to the size required to carry more than 600-700 passengers raises several questions. To explore these and a number of related issues, a team of Boeing, university, and NASA engineers was formed under the auspices of the NASA Advanced Concepts Program. The results of a Research Analysis focused on a large, unconventional transport airplane configuration for which Boeing has applied for a patent are the subject of this report. It should be noted here that this study has been conducted independently of the Boeing New Large Airplane (NLA) program, and with the exception of some generic analysis tools which may be common to this effort and the NLA (as will be described later), no explicit Boeing NLA data other than that published in the open literature has been used in the conduct of the study reported here.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-201614 , NAS 1.26:198351 , D6-81724
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Modeling of heavy-gas effects on airfoil flows (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermodynamic models were constructed for a calorically imperfect gas and for a non-ideal gas. These were incorporated into a quasi one dimensional flow solver to develop an understanding of the differences in flow behavior between the new models and the perfect gas model. The models were also incorporated into a two dimensional flow solver to investigate their effects on transonic airfoil flows. Specifically, the calculations simulated airfoil testing in a proposed high Reynolds number heavy gas test facility. The results indicate that the non-idealities caused significant differences in the flow field, but that matching of an appropriate non-dimensional parameter led to flows similar to those in air.
    Keywords: AERODYNAMICS
    Type: NASA-CR-190357 , NAS 1.26:190357
    Format: application/pdf
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  • 7
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    Calculation methods for rotor wake formation in forward flight (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The primary focus of this research centered on improving the vorticity-capturing properties of Eulerian flow solvers in convection-dominated flows. The work was motivated by the fact that excessive numerical diffusion observed in current Euler solvers on grids of feasible size is a major obstacle to accurately computing the flow about helicopter rotors, especially in the forward flight case. The work was originally supported by NASA Grant NAG2-421 for two years. The research then continued for four more years under an ONR contract. The research goal of reduction of numerical diffusion in Euler solvers remained the same, although the target application was now the prediction of internal vortical secondary flows. This was part of a larger ONR-sponsored research program at MIT aimed at reducing the noise of turbopumps. The research work culminated in the PhD thesis titled 'A Coupled Eulerian/Lagrangian Method for the Solution of Three-Dimensional Vortical Flows'.
    Keywords: AERODYNAMICS
    Type: NASA-CR-196787 , NAS 1.26:196787
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    An Eulerian/Lagrangian coupling procedure for three-dimensional vortical flows (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A coupled Eulerian/Lagrangian method is presented for the reduction of numerical diffusion observed in solutions of 3D vortical flows using standard Eulerian finite-volume time-marching procedures. A Lagrangian particle tracking method, added to the Eulerian time-marching procedure, provides a correction of the Eulerian solution. In turn, the Eulerian solution is used to integrate the Lagrangian state-vector along the particles trajectories. While the Eulerian solution ensures the conservation of mass and sets the pressure field, the particle markers describe accurately the convection properties and enhance the vorticity and entropy capturing capabilities of the Eulerian solver. The Eulerian/Lagrangian coupling strategies are discussed and the combined scheme is tested on a constant stagnation pressure flow in a 90 deg bend and on a swirling pipe flow. As the numerical diffusion is reduced when using the Lagrangian correction, a vorticity gradient augmentation is identified as a basic problem of this inviscid calculation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 93-3370 , In: AIAA Computational Fluid Dynamics Conference, 11th, Orlando, FL, July 6-9, 1993, Technical Papers. Pt. 2 (A93-44994 18-34); p. 784-796.
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A High Altitude-Low Reynolds Number Aerodynamic Flight Experiment (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: A sailplane is currently being developed at NASA's Dryden Flight Research Center to support a high altitude flight experiment. The purpose of the experiment is to measure the performance characteristics of an airfoil at altitudes between 100,000 and 70,000 feet at Mach numbers between 0.65 and 0.5. The airfoil lift and drag are measured from pilot and static pressures. The location of the separation bubble and vortex shedding are measured from a hot film strip. The details of the flight experiment are presented. A comparison of several estimates of the airfoil performance is also presented. The airfoil, APEX-16, was designed by Drela (MIT) with his MSES code. A two dimensional Navier-Stokes analysis has been performed by Tatineni and Zhong (UCLA) and another at the Dryden Flight Research Center. The role these analysis served to define the experiment is discussed.
    Keywords: Aerodynamics
    Type: Applied Aerodynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Design and Predictions for a High-Altitude (Low-Reynolds-Number) Aerodynamic Flight Experiment (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000 to 100,000 ft), low Reynolds numbers (200,000 to 700,000), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pitot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented. Several predictions of the airfoil performance are also presented. Mark Drela from the Massachusetts Institute of Technology designed the APEX-16 airfoil, using the MSES code. Two-dimensional Navier-Stokes analyses were performed by Mahidhar Tatineni and Xiaolin Zhong from the University of California, Los Angeles, and by the authors at NASA Dryden.
    Keywords: Aerodynamics
    Type: NASA/TM-1999-206579 , NAS 1.15:206579 , H-2340 , AIAA Paper 99-3183 , 14th Computational Fluid Dynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States|17th Applied Aerodynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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