Simulating Magneto-Aerodynamic Actuator
Abstract
A hypersonic flow control by amplifying an electromagnetic perturbation through viscous-inviscid interaction has been developed and verified by experimental observations. The electromagnetic perturbation is generated by a near-surface direct current discharge. The Joule heating and Lorentz acceleration induce an oblique shock over the localized plasma domain and produce a high-pressure plateau for flow control. The interdisciplinary phenomenon has been successfully simulated by solving the three-dimensional, magneto-fluid-dynamic equations with a weakly ionized gas model based on the drift-diffusion theory. The side-by-side computational and experimental research effort has demonstrated that the magneto-fluid- dynamic interaction is an innovative and effective mechanism of the virtual leading edge strake and virtual variable cross-sectional area inlet cowls for hypersonic flow control. Technology transfer has also been accomplished through personal interaction with personnel of Air Force Research Laboratory and NASA National Aerospace Institute.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 20, 2007
- Accession Number
- ADA476149
Entities
People
- Joseph J. Shang
Organizations
- Wright State University