Active flow control via finite-span synthetic jet (SJ) actuators was used to affect the aerodynamic loads on a half model of a chined forebody delta wing. Three different SJ orientations were explored, employing surface-normal SJs, horizontal SJs, or SJs angled 45 deg away from the leading edge relative to the normal direction. Six cases were explored, one with each jet individually actuated and one with both jets actuated together, each with and without pulse-modulation waveform having a modulation frequency corresponding to the helical mode frequency. In all cases, the synthetic jets were activated with ( per jet). Aerodynamic load measurements were conducted to explore the effects of flow control, along with detailed flowfield measurements using to shed light on the reasons for these effects. It was found that the surface-normal SJs had a much larger effect on the aerodynamic coefficients than the other two SJ orientations. This resulted in an increase in nose-down pitching moment, increased lift and increased drag, as well as reduced wandering of the chine and wing vortices. In addition, pulse modulation made the actuation much more energy-efficient as the modulation caused the helical mode to lock onto the actuation frequency.
Flow Control over a Generic Tailless Chined Forebody Delta Wing
AIAA Journal ; 1-14
2025-01-01
Article (Journal)
Electronic Resource
English