Plasma-Actuated Flow Control of Hypersonic Crossflow-Induced Boundary-Layer Transition

The purpose of this research was to design, fabricate, and test a plasma-based active flow-control system to accelerate and delay crossflow-induced boundary-layer transition on a cone at an angle of attack at Mach 6 under quiet-flow conditions. A model with interchangeable nosetips was designed and...

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Veröffentlicht in:	AIAA journal 2020-05, Vol.58 (5), p.2093-2108
Hauptverfasser:	Yates, Harrison B, Matlis, Eric H, Juliano, Thomas J, Tufts, Matthew W
Format:	Artikel
Sprache:	eng
Schlagworte:	Active control Actuators Aerial thermography Aerodynamics Amplitudes Angle of attack Boundary layer transition Computational fluid dynamics Cross flow Engineering Engineering, Aerospace Flow control Fluid flow Infrared imaging Nose tips Plasma Polyether ether ketones Science & Technology Stainless steels Technology Transducers Wavelengths
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