Numerical investigation of hypersonic flow with repetitive-pulsed plasma actuators. (July 2018)

• Record Type: Journal Article
• Authors: Wang, Chin-Cheng; Hsu, Li-Chung
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 232:Number 9(2018)
• Page Start: 1715
• Page End: 1724
• Publication Date: 2018-07
• Subjects: Repetitive-pulsed discharges -- power deposition -- hypersonic flow control -- bow shock wave -- plasma actuators; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410017703417
• Languages: English
• ISSNs: 0954-4100

Abstract

Repetitive-pulsed plasma actuators have become the key enabler for flights in the hypersonic flow control. A numerical study focuses on the effect of the repetitive-pulsed plasma actuators at Mach 6. The geometric effects of circular, square, and triangular cylinders as well as a sphere on the aerodynamic performance are considered in the present study. For flow over the circular cylinder and sphere, shock control by repetitive-pulsed discharges is investigated, respectively. The baseline results are successfully validated with the theoretical and published numerical values for flow past a circular cylinder at Mach 6. Without flow control, results show that the shapes of the triangular cylinder and sphere have much smaller high-pressure regions compared to that of the square and circular cylinders. With repetitive-pulsed plasma, the time-average drag reduction has been reduced by a maximum of 0.8% and the stagnation pressure ratio is reduced by 2.1% for Mach 6 flow over a circular cylinder. Thus, this research shows a great benefit of repetitive-pulsed discharges to the state-of-the-art in high-speed flight design.