Numerical analysis and optimization of three-dimensional MHD controlled inlets

Design and optimization of three-dimensional MHD controlled inlets by means of numerical simulation were devoted in the present study. An airframe/propulsion integrated module was first established for a waverider-based hypersonic vehicle at design Mach value of 6. Utilizing this generic configuration, a MHD-based technique for large-scale inlet flow control was studied at the off-designed Mach value of 8.5. Using mass flow rate as an optimization criterion, an MHD generator possessing reasonable design parameters would restore the flow field and shock system as if the scramjet was operated under the design condition, and made the flow characteristics at the combustor entrance more favorable when flying at higher Mach numbers than the design value. In order to bring shocks back to the cowl lip, extracting more electric power from the external MHD generator, and improving the performances of the combustor entrance, the load factor should be elevated.