Abstract
Active flow control (AFC) has gained a great deal of attention in recent flow control research and applications. Use of AFC has shown improvement in aircraft performance by reduction in drag and increase in lift. The objective of the present study is to understand the physical mechanisms behind drag reduction. Two configurations that are prime candidates for drag reduction through separation control have been studied. The first configuration is a NACA 0036 airfoil whose shape is similar to that of a helicopter rotor hub covered with a shroud. The second is a bluff body reminiscent of a backward facing step. Due to the bluff body shape, in both cases, separation occurs near the aft end of the body. These are thus suitable candidates for studying flow control and drag reduction. Active flow control at a fixed chord location has been studied and the flow field examined for underlying causes. Comparisons to experiments are given wherever possible. The effect of the jet on turbulent quantities has been analyzed. Based on this analysis, possible causes of drag reduction have been hypothesized.
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