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  • 1980-1984  (3)
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  • 1
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    Unknown
    The use of hot-wire anemometry in transonic periodic flow (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The unsteady wake profiles of an airfoil with an oscillating flap were measured in the NASA Ames 11 x 11-foot transonic wind tunnel. Laser Doppler Velocimetry (LDV) and holography techniques were used in limited region where optical accessability is available. X-hot-film wire was used to measure the wake profiles in the complete region to obtain magnitude and direction of the flow. A thorough calibration was carried out to determine the sensitivity coefficients of the hot-wire in three different tunnels at transonic speeds. A calculation procedure is established to resolve the hot-wire signals at transonic speeds and applied in the measurements of steady and periodic wake profiles. The effect of flow incidence on the hot-wire signals is evaluated and incorporated in the analyses. Typical hot-wire results are compared with the results of LDV, holography and pitot-static tube embedded with Kulite transducers.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 84-0597
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Flow measurements of an airfoil with deflected spoiler (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Spoilers are used as an effective control surface in various stages of flight. The steady and unsteady flow characteristics change with incidence and spoiler angle. An experimental investigation is undertaken to understand the flow phenomena. Typical boundary layer and wake profiles at various incidences and spoiler angles are presented and discussed. A laminar separation is observed at low incidence and high spoiler angle. At incidence, a turbulent boundary layer develops and separation point moves downstream. Generally the wake profiles are asymmetric. When different length scales are used, the profiles become self-similar and symmetric. The importance of laser velocimetry in the reverse flow region is demonstrated by comparing the preliminary LDV measurements with the hot-wire results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-0365 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Unsteady wake measurements of an oscillating flap at transonic speeds (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The steady and unsteady wake profiles of an airfoil with an oscillating flap were measured at nominal free stream Mach number of 0.8 in the NASA Ames 11 x 11-foot wind tunnel. The instantaneous wake velocity and pressure profiles at four axial locations are presented up to one chord length from the trailing edge. Both fundamental harmonic frequency and typical time history data are presented to observe the effects of airfoil incidence and flap angle. The drag coefficient obtained from the wake pressure measurements is compared with that obtained from the airfoil pressure distribution.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1563
    Format: text
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    NASA TECHNICAL REPORTS
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