Computational investigations were carried out on an advanced serpentine jetengine inlet duct to understand the development and propagation of secondary flowstructures. Computational analysis which went in tandem with experimentalinvestigation was required to aid secondary flow control required for enhanced pressurerecovery and decreased distortion at the engine face. In the wake of earlier attempts withmodular fluidic actuators used for this study, efforts were directed towards optimizingthe actuator configurations. Backed by both computational and experimental resources,many variations in the interaction of fluidic actuators with the mainstream flow wereattempted in the hope of best controlling secondary flow formation. Over the length ofthe studies, better understanding of the flow physics governing flow control for 3Dcurved ducts was developed.Blowing tangentially, to the wall at the bends of the S-duct, proved extremelyeffective in enforcing active flow control. At practical jet momentum coefficients,significant improvements characterized by an improved pressure recove ry of 37% and adecrease in distortion close to 90% were seen.
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