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  • 1
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    Optimization of multi-element airfoils for maximum lift (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two theoretical methods are presented for optimizing multi-element airfoils to obtain maximum lift. The analyses assume that the shapes of the various high lift elements are fixed. The objective of the design procedures is then to determine the optimum location and/or deflection of the leading and trailing edge devices. The first analysis determines the optimum horizontal and vertical location and the deflection of a leading edge slat. The structure of the flow field is calculated by iteratively coupling potential flow and boundary layer analysis. This design procedure does not require that flow separation effects be modeled. The second analysis determines the slat and flap deflection required to maximize the lift of a three element airfoil. This approach requires that the effects of flow separation from one or more of the airfoil elements be taken into account. The theoretical results are in good agreement with results of a wind tunnel test used to corroborate the predicted optimum slat and flap positions.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt.1; p 237-253
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of simulated forward airspeed on small-scale-model externally blown flap noise (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Noise tests were conducted on a small-scale model of an externally blown flap lift augmentation system. The nozzle/wing model was subjected to external flow that simulated takeoff and landing flight velocities by placing it in a 33-centimeter-diameter free jet. The results showed that external flow attenuated the noise associated with the various configurations tested. The amount of attenuation depended on flap setting. More attenuation occurred with a trailing-flap setting of 20 deg than with one of 60 deg. Noise varied with relative velocity as a function of the trailing-flap setting and the angle from the nozzle inlet.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8305 , E-8697
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Noise generated by impingement of turbulent flow on airfoils of varied chord, cylinders, and other flow obstructions (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Noise spectra were measured in three dimensions for several surfaces immersed in turbulent flow from a jet and over a range of flow conditions. The data are free field and were corrected to remove the small contributions of jet noise, atmospheric attenuation and feedback tones. These broadband data were compared with the results of available theories which are only strictly applicable to simple geometries over a limited range of conditions. The available theories proved to be accurate over the range of flow, chord length, thickness, angle of attack, and surface geometries defined by the experiments. These results apply to the noise generated by fixed surfaces in engine passages, the lifting surfaces of aircraft and also to fan noise.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-504 , Aero-Acoustics Conference; Jul 20, 1976 - Jul 23, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Lip noise generated by flow separation from nozzle surfaces (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flow separation from nozzle surfaces can be a source of significant noise in addition to the jet noise. When no flow separation region exists only jet noise is observed at every angle, for velocities down to 120 m/sec, with both low and high levels of initial turbulence. Intense nearly periodic turbulence and noise is caused by flow separation from the thin core nozzle lip of a coaxial nozzle. This can be described by a combination of aeolian tone and trailing edge noise theory. Noise caused by flow separation from the surfaces of other nozzle geometries has somewhat different characteristics.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-3 , Aerospace Sciences Meeting; Jan 26, 1976 - Jan 28, 1976; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
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