Accession Number ADA586561
Title Hypersonic Flow over a Cylinder with a Nanosecond-Pulse Electrical Discharge.
Publication Date 2013
Media Count 21p
Personal Author I. Adamovich J. Poggie M. Nishihara N. J. Bisek
Abstract A computational study of Mach 5 air over a cylinder with a dielectric barrier discharge actuator was performed. The actuator was pulsed at nanosecond time scales, and it rapidly added thermal energy to the flow, creating a shock wave that traveled away from the pulse source. As the shock wave traveled upstream, it interacted with the standing bow-shock, and temporarily increased the bow-shock standoff distance. This phenomenon was also observed experimentally through phase-locked schlieren photography. This paper aims to reproduce flow phenomena observed in the experiment using high-fidelity computations in order to provide additional insight into the shock-shock interaction, and subsequent effect on the cylinder, through a reduced-order phenomenological model of the actuator. A three-dimensional simulation of the experiment was able to accurately capture the complex cylinder/tunnel-sidewall interaction, and to replicate the changes in the flow produced by the nanosecond dielectric barrier discharge. The results show that the device was very effective at moving the standing bow-shock for a minimal energy budget.
Keywords Actuators
Computational fluid dynamics
Cylindrical bodies
Dielectrics
Electric discharges
Energy deposition
Hypersonic flow
Lemans code
Mach number
Ns dbd(Nanosecond dielectric barrier discharge)
Pulses
Schlieren photography
Shock
Thermal energy


 
Source Agency Non Paid ADAS
NTIS Subject Category 41J - Tooling, Machinery, & Tools
46 - Physics
46B - Fluid Mechanics
Corporate Author Air Force Research Lab., Wright-Patterson AFB, OH. Air Vehicles Directorate.
Document Type Journal article
Title Note Journal article.
NTIS Issue Number 1405
Contract Number LRIR-12RB09COR

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