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  • 1
    facet.materialart.
    Unbekannt
    Resistance of Certain Grain Sorghum Hybrids to Bird Damage in Louisiana 1 (1970)
    Wiley
    Details
    Publikationsdatum: 1970-03-01
    Print ISSN: 0002-1962
    Digitale ISSN: 1435-0645
    Thema: Land- und Forstwirtschaft, Gartenbau, Fischereiwirtschaft, Hauswirtschaft
    Publiziert von Wiley
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    AKTUELLE ARTIKEL
  • 2
    facet.materialart.
    Unbekannt
    Measurement of pressures and heat transfer by FM telemetry. (1966)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-11
    Beschreibung: Pressure and heat transfer measurement by FM TELEMETRY for models flying freely in hypersonic wind tunnel streams
    Schlagwort(e): INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 3
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    Unbekannt
    A new facility and technique for two-dimensional aerodynamic testing (1983)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-18
    Beschreibung: Previously cited in issue 10, p. 1554, Accession no. A82-24677
    Schlagwort(e): RESEARCH AND SUPPORT FACILITIES (AIR)
    Materialart: (ISSN 0021-8669)
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 4
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    Unbekannt
    Simulation of turbulent transonic separated flow over an airfoil (1975)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: A code developed for simulating high Reynolds number transonic flow fields of arbitrary configuration is described. This code, in conjunction with laboratory experiments, is used to devise and test turbulence transport models which may be suitable in the prediction of such flow fields, with particular emphasis on regions of flow separation. The solutions describe the flow field, including both the shock-induced and trailing-edge separation regions, in sufficient detail to provide the profile and friction drag.
    Schlagwort(e): AERODYNAMICS
    Materialart: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 419-436
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 5
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    Unbekannt
    A technique for launching free-flying models in conventional wind tunnels. (1966)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-30
    Beschreibung: Launching device for free flying models in conventional wind tunnels consisting of split hollow shell enclosing model
    Schlagwort(e): FACILITIES, RESEARCH, AND SUPPORT
    Materialart: AIAA PAPER 66-773
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 6
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    Static and dynamic pressure measurements on a NACA 0012 airfoil in the Ames High Reynolds Number Facility (1985)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The supercritical flows at high subsonic speeds over a NACA 0012 airfoil were studied to acquire aerodynamic data suitable for evaluating numerical-flow codes. The measurements consisted primarily of static and dynamic pressures on the airfoil and test-channel walls. Shadowgraphs were also taken of the flow field near the airfoil. The tests were performed at free-stream Mach numbers from approximately 0.7 to 0.8, at angles of attack sufficient to include the onset of buffet, and at Reynolds numbers from 1 million to 14 million. A test action was designed specifically to obtain two-dimensional airfoil data with a minimum of wall interference effects. Boundary-layer suction panels were used to minimize sidewall interference effects. Flexible upper and lower walls allow test-channel area-ruling to nullify Mach number changes induced by the mass removal, to correct for longitudinal boundary-layer growth, and to provide contouring compatible with the streamlines of the model in free air.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-2485 , A-85100 , NAS 1.60:2485
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 7
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    Unbekannt
    An experimental and computational investigation of the flow field about a transonic airfoil in supercritical flow with turbulent boundary-layer separation (1976)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A combined experimental and computational research program is described for testing and guiding turbulence modeling within regions of separation induced by shock waves incident in turbulent boundary layers. Specifically, studies are made of the separated flow the rear portion of an 18%-thick circular-arc airfoil at zero angle of attack in high Reynolds number supercritical flow. The measurements include distributions of surface static pressure and local skin friction. The instruments employed include highfrequency response pressure cells and a large array of surface hot-wire skin-friction gages. Computations at the experimental flow conditions are made using time-dependent solutions of ensemble-averaged Navier-Stokes equations, plus additional equations for the turbulence modeling.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-TM-X-73157 , A-6690
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 8
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    Unbekannt
    A design method for entrance sections of transonic wind tunnels with rectangular cross sections (1975)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A mathematical technique developed to design entrance sections for transonic or high-speed subsonic wind tunnels with rectangular cross sections is discribed. The transition from a circular cross-section setting chamber to a rectangular test section is accomplished smoothly so as not to introduce secondary flows (vortices or boundary-layer separation) into a uniform test stream. The results of static-pressure measurements in the transition region and of static and total-pressure surveys in the test section of a pilot model for a new facility at the Ames Research Center are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-62490 , A-6293
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unbekannt
    Supercritical flow about a thick circular-arc airfoil (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The supercritical flow about a biconvex circular-arc airfoil is being thoroughly documented at Ames Research Center in order to provide experimental test cases suitable for guiding and evaluating current and future computer codes. The effects of angle of attack, effects of leading and trailing-edge splitter plates, additional unsteady pressure fluctuation (buffeting) measurements and glow-field shadowgraphs, and application of an oil-film technique to display separated-wake streamlines were studied. Computed and measured pressure distributions for steady and unsteady flows, using a recent computer code representative of current methodology, are compared. It was found that the numerical solutions are often fundamentally incorrect in that only strong (shock-polar terminology) shocks are captured, whereas experimentally, both strong and weak shock waves appear.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78549 , A-7693
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unbekannt
    A new facility and technique for two-dimensional aerodynamic testing (1982)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The design and operational characteristics of a new test leg for the High Reynolds Number Facility at Ames Research Center are presented, and the unique features of a test section for obtaining two-dimensional airfoil data are reviewed. The new facility operates at unit Reynolds numbers ranging from 1,000,000/ft to 30,000,000/ft. Boundary-layer suction panels are used in the test section (16 in. wide by 24 in. high) to minimize side-wall interference effects. Flexible, easily adjustable upper and lower walls allow test-channel area-ruling so as to nullify Mach-number changes induced by mass removal, to correct for longitudinal boundary-layer growth, and to provide contouring compatible with the streamlines of the model in free air.
    Schlagwort(e): RESEARCH AND SUPPORT FACILITIES (AIR)
    Materialart: AIAA PAPER 82-0608 , In: Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
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