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  • AERODYNAMICS  (17)
  • 1970-1974  (12)
  • 1960-1964  (4)
  • 1945-1949  (1)
  • 1
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    Aerodynamic and performance characteristics of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteristics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a particular externally blown flap configuration is presented. The following specific effects are analyzed: (1) induced aerodynamics, (2) static turning, (3) flap span and deflection, and (4) engine size and chord flap.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 43-54
    Format: text
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  • 2
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    Two-dimensional supersonic wing theory (1948)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 325-340
    Format: application/pdf
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  • 3
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    ECONOMY OF SPACE FLIGHT (1960)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-10
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-51385 , MTP-M-FPO-60-2
    Format: text
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  • 4
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    Interaction of grid turbulence with a uniform mean shear (1970)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Grid turbulence interaction with uniform mean shear flow, examining initial disturbance length scale effects
    Schlagwort(e): AERODYNAMICS
    Materialart: ; YAL SOCIETY (
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    Low speed wind tunnel flow field results for JT8D refan engines on the Boeing 727-200 (1974)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Low speed flow angularity results are presented showing flow direction at the nacelle locations on the Boeing 727-200. Flow angle probes (yawheads) were used for measurements at side and center inlet positions on the aft fuselage. A range of flap settings were tested with flap angles of 0 deg, 15 deg, and 40 deg selected for investigation.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-134630 , D6-43098
    Format: application/pdf
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  • 6
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    Inverse problem approach to the design of short two-dimensional diffusers. (1972)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 72-WA/GT-6 , Winter Annual Meeting of the American Society of Mechanical Engineers; Nov 26, 1972 - Nov 30, 1972; New York, NY
    Format: text
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  • 7
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    An experimental investigation of base heating on typical Mars entry body shapes. (1972)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Hypersonic experiments on wire supported high angle blunt cones were conducted to determine the base heating characteristics. Heating distributions were obtained for several base configurations with variations in free stream Reynolds Number and gas composition. The dependence of the heating in the base region on angle of attack was also investigated. It was found that gas composition effects can be accounted for by comparison at equal Reynolds Number. Angle of attack effects can result in either increasing or decreasing base heating depending upon the location in the base region.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 72-317 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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  • 8
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    A wind tunnel investigation of the wake near the trailing edge of a deflected externally blown flap (1974)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The model tested was a general research model of a swept-wing, jet-powered STOL transport with externally blown flaps. The model was tested with four engine simulators mounted on pylons under the wing. Tests were conducted in the V/STOL tunnel over an angle of attack range of 0 deg to 16 deg and a thrust coefficient range from 0 to approximately 4 at a Reynolds number of 0.461 x 1 million based on the wing reference chord. The results of this investigation are presented primarily as plots of the individual velocity vectors obtained from the wake survey. These data are used to extend an earlier analysis to isolate the effects of the engine thrust on the behavior of the flow at the flap trailing edge. Results of a comparison with a jet-flap theory are also shown.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-3079 , L-9665
    Format: application/pdf
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  • 9
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    The design and performance of axially symmetrical contoured wall diffusers employing suction boundary layer control (1974)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents a procedure for the design and the performance prediction of axially symmetrical contoured wall diffusers employing suction boundary layer control. An inverse problem approach was used in the potential flow design of the diffuser wall contours. The experimentally observed flow characteristics and the stability of flows within the diffuser are also described. Guidelines for the design of low suction (less than 10 percent of the inlet flow) and thus high effectiveness contoured wall diffusers are also provided based on the results of the experimental program.
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 74-GT-152 , Gas Turbine Conference and Products Show; Mar 30, 1974 - Apr 04, 1974; Zurich; Switzerland
    Format: text
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  • 10
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    GOALS AND THE UNIVERSITY (1963)
    In:  CASI
    Details
    Publikationsdatum: 2006-10-26
    Beschreibung: Goals of space science program and relationship of universities to space exploration - nasa program
    Schlagwort(e): AERODYNAMICS
    Format: text
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