Separation control of the three-dimensional flow over the aft segment of a NASA Rotor-Body-Interaction (ROBIN) rotorcraft fuselage is investigated in wind-tunnel experiments using arrays of miniature combustion-based actuators. Successive pulsed actuation is effected by momentary jets each having a characteristic time scale O[1 ms] that is an order of magnitude shorter than the convective time scale of the flow. The actuators are placed upstream of the transition ramp between the ROBIN’s fuselage and the tail boom. The jet-induced interactions with the massively separated crossflow over the ramp and their effects on the global aerodynamic forces and moments are investigated using high-resolution particle image velocimetry that is acquired phase-locked to the actuation waveform in conjunction with simultaneous force and moment measurements using an onboard load cell. The present investigations show that symmetric actuation about the model’s centerline can significantly mitigate separation, lead to a reduction in drag and lift, and alter the pitching moment. Asymmetric actuation, and consequently nonuniform attachment, can induce significant side forces as well as roll and yaw moments that may be exploited for steering and improved flight maneuverability.
Pulsed Actuation Control of Flow Separation on a ROBIN Rotorcraft Fuselage
AIAA journal ; 54 , 10
2016
Aufsatz (Zeitschrift)
Englisch
TRANSITORY CONTROL OF AERODYNAMIC FORCES ON A ROBIN FUSELAGE USING PULSED ACTUATION
British Library Conference Proceedings | 2011
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