Interest has recently been renewed in the use of distributed suction for the production of laminar flow over substantial areas of the surface of aircraft wings and engine nacelles. Suction may be most efficiently applied by using a number of independently controllable panels through which fluid is withdrawn. The need to determine the distribution of suction flow rates the results in a given streamwise location of boundary-layer transition with minimum power consumed in providing suction gives rise to a nonlinearly constrained optimization problem.
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