Three-dimensional design and numerical simulation of magnetohydrodynamic controlled hypersonic inlets

Abstract

The purpose of this study is to perform numerical simulation for the design and optimization of three-dimensional magnetohydrodynamic (MHD) controlled hypersonic inlets. An airframe/propulsion integrated module was first established for a waverider-based hypersonic vehicle at design Mach number of 6. Using this generic configuration, an MHDbased technique for large-scale inlet flow control is studied at the off-designed Mach value of 8.5. The results indicate that the inlet mass flowrate can act as an optimization criterion. Using a proper value of mass flowrate, an MHD generator possessing reasonable design parameters can effectively restore the flow field shock structure, i.e. shock-on-lip condition and improves the flow field characteristics at the combustor entrance at higher Mach number than the design value. The results further reveal that the MHD effect on the flow with higher load factor helps to extract more electric power from the external MHD generator and also helps in improving the performance of the combustor entrance.

Comparison research of two different improved methods in the 2D hypersonic inlet’s design

“…Additionally, the performance of the inlet decrease greatly and perhaps work instable at the off-design conditions. 3 Up to now, the researchers have proposed varieties of improved methods to improve inlet’s comprehensive performance, such as variable geometry, 4,5 porous bleeding, 6 boundary layer suction, 7 MHD control method, 9 plasma control method, 9 slot bleeding, 1,10–26 isentropic expansion arc surface 26,27 and so on. Among these control methods, the slot bleeding and isentropic expansion arc surface are the most simple and efficient improved methods, because they do not need any additional energy or control devices.…”