A numerical investigation was conducted to explore the potential of magnetically accelerated surface discharges to control the flow over reentry vehicles at high angle of attack. The baseline geometry and test conditions were selected based on experiments: a blunt-nosed elliptic cone with a half-angle along the major axis of 10 deg, a Mach number of 14.5, a Reynolds number based on a length of 36,000, and an angle of attack of 60 deg. A phenomenological model was developed, based on experiments and computations, to simulate the effects of magnetically accelerated surface discharges on the elliptic cone flow. Control was applied near the leeward-side crossflow separation line, and several actuator configurations were considered, include symmetric and asymmetric patterns and inboard and outboard forces. There were substantial changes in the leeward-side flow structure with actuation. Moments generated about the pitch, yaw, and roll axes were quantified, along with the corresponding heat transfer penalty and actuator power consumption.
Control of High-Angle-of-Attack Reentry Flow with Plasma Actuators
Journal of Spacecraft and Rockets ; 50 , 2 ; 337-346
2013-01-18
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Control of High-Angle-of-Attack Reentry Flow with Plasma Actuators
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