Flow field measuremnts of an airfoil with deflected spoiler using a two-component LDV system
Foreman, Michael J.
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The primary goals of this thesis included developing a computer-integrated LDV system, utilizing the LDV system to measure the mean and fluctuating quantities of the flow field of an airfoil-spoiler system, and comparing the results of the experiment with previous hot-wire anemometry results. The experiment was conducted in the NASA Ames 11 cm x 25 cm indraft tunnel. A two-component LDV system was developed and set up, and measurements were obtained along the upper surface of the airfoil (ahead of and behind the spoiler) as well as in its wake, close to the trailing edge. Mean velocity profiles and turbulent stresses were calculated and comparisons were made with previous hot-wire experiments. It was shown that the hot-wire technique is not as accurate as the LDV in highly turbulent regions of the flow field. The hot-wire results are also not reliable in the near wake region due to the inherent reverse flow. In other, less turbulent, regions of the flow field where there is no reverse flow, good agreement between previous hot-wire data and present experimental results was found.
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NPS Report NumberNPS-67-86-008
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