Heat Flux Gage Studies of Compressible Dynamic Stall
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Compressible dynamic stall was studied using 148 closely spaced heat flux gages distributed over the surface of an oscillating, 6-inch chord NACA 0012 airfoil. The study has revealed the various surface flow features of compressible dynamic stall and their changes under different flow conditions. It has also provided a description of the events that are precursors to dynamic stall onset. The imprint of a leading edge shock has been recorded for the first time in the surface flow signature. The data indicate that extremely large gradients develop prior to onset of dynamic stall, pointing to a singular event that drives the flow into the stalled state.
The article of record as published may be found at http://dx.doi.org/10.2514/6.2002-291
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