Experimental Investigation of Magnetohydrodynamic Flow Interaction for Hypersonics and Planetary Entry

High-speed, continuous trajectory control during hypersonic flight is of importance to both planetary missions and national security. However, current control methods are limited due to the intense thermal and structural loads during hypersonic flight. Because the vehicle is moving hypersonically, the flow around the vehicle is potentially ionized, and magnetohydrodynamic (MHD) flow interaction can leverage this ionized plasma to maneuver the vehicle. Specifically, an onboard magnet can interact with the ionized plasma, inducing a Lorentz force on the vehicle, allowing for the manipulation of the total lift force, drag force, and/or control moments on the vehicle. Active trajectory control using MHD flow control requires a significant power source to operate the non-permanent magnet; however, the free electrons in the flow can be used to power a usable electric current via MHD energy generation. Thus, MHD flow control with MHD energy generation serves as a promising option for hypersonic flight because it allows for not only self-powering, high-speed, continuous trajectory control with requiring aerodynamic control surfaces, center of mass control, or reaction control systems, but it also extends control authority to higher altitudes, reducing thermal and structural requirements. While experimental studies have documented the benefits of MHD energy generation or MHD flow interaction alone, this investigation will experimentally test simultaneous MHD energy generation and MHD drag augmentation and observe the effect collecting energy has on inducing drag. Preliminary results and estimates find that the current produced is on the same order of magnitude with or without drag augmentation and that the drag induced agrees with computational estimates, even with simultaneous MHD energy generation.