Abstract
Magnetohydrodynamic (MHD) control of hypersonic laminar separation flows is investigated in this paper. A series of numerical simulations over various geometry configurations, namely, a compression corner and a double wedge ramp hypersonic inlet, have been conducted by application of an external electromagnetic field. Results show that the performance of MHD separation flow control is mainly determined by flow acceleration of the Lorentz force directed in the streamwise direction. The Joule heating term always brings negative effects on the MHD separation flow control and increased the static pressure locally, where the electromagnetic field is applied. With an external electromagnetic field applied, the low velocity fluid in the boundary layer can be accelerated. Moreover, there exists a best location for the MHD zone to be applied and completely eliminate the separation of the flow from the surface.
Highlights
Some of the most serious and challenging problems encountered by the designers of hypersonic vehicles arise because of the severity of the heating loads and the steepness of the flow gradients that are generated in shock wave boundary layer interaction (SWBLI) regions
To discuss the effect of the electromagnetic field for hypersonic SWBLIs in laminar flows, this paper focuses on two configurations
The study provides a foundation for future developments of a comprehensive tool for hypersonic MHD separation flow control techniques
Summary
Some of the most serious and challenging problems encountered by the designers of hypersonic vehicles arise because of the severity of the heating loads and the steepness of the flow gradients that are generated in shock wave boundary layer interaction (SWBLI) regions. Recent developments in artificial ionization techniques and improvements in superconducting materials have resulted in consideration of the electromagnetic field as a tool for modifying SWBLI in the hypersonic flow regime [3, 4]. This flow control system has so many advantages [5, 6] in that it is reusable, easy to be switched on-off, highly reliable, and does no harm to the aerodynamic configuration of the object aircraft. The study provides a foundation for future developments of a comprehensive tool for hypersonic MHD separation flow control techniques
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