Wind tunnel tests were conducted to determine the transition region on the 76 deg Flat Plate Delta Wing model in the basic Aerodynamics Research Tunnel (BART) facility at the NASA-LaRC for a range of Reynolds numbers and angles of attack. This was accomplished by means of a special multi-element, thin-film sensor mounted on the suction surface of the Delta Wing operated by a bank of Constant Voltage Anemometers (CVA). The signals from the CVA were processed to obtain RMS, Intermittency distributions and any frequency spectra information in the measurements. The transition detection tests with hotfilm sensors were successful in demarcating the transition region and providing important spectral information. The results show the effect of angle of attack and Reynolds number variation on the extent of the transition region on the suction surface of the delta wing model.
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