This research describes a computational study undertaken to determine the effect of a flow control mechanism and its associated\naerodynamics for a finned projectile. The flow control system consists of small microflaps located between the rear fins of\nthe projectile. These small microflaps alter the flow field in the aft finned region of the projectile, create asymmetric pressure\ndistributions, and thus produce aerodynamic control forces and moments. A number of different geometric parameters, microflap\nlocations, and the number of microflaps were varied in an attempt tomaximize the control authority generated by the flaps. Steadystate\nNavier-Stokes computations were performed to obtain the control aerodynamic forces and moments associated with the\nmicroflaps. These results were used to optimize the control authority at a supersonic speed,
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