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To investigate the influence of plasma actuator dispose position and control parameters on aircraft lift enhancement,wind tunnel experiment was taken on flying wing aircraft.AC and nanosecond pluse plasma power were used separately.The result indicates that the plasma actuator can efficiently increase the maximum lift coefficient and defer the occurrence of stall while have small impact on drag coefficient of flying wing aircraft.The actuator disposed parallel to the aircraft leading edge was found to be more effective while placed at leading edge provided the best performance on lift enhancement.