Date of Award
Master of Science in Aeronautical Engineering
Department of Aeronautics and Astronautics
Richard J. McMullan, PhD
The effect of magnetogasdynamic (MGD) interactions on flow acceleration and thrust in a scramjet accelerator/nozzle are examined numerically at a free-stream flight condition of Mach 8. The parameters of conductivity pattern and load factor are varied in both inviscid and viscous flow regimes with the intent of increasing axial force exerted on the flow through a scramjet accelerator. The numerical code solves the Navier-Stokes equations with additional source terms for the MGD forces and energy interactions. An accelerating Lorentz force is applied to the flow resulting from a constant magnetic field and an electric field produced by two continuous side wall electrodes. The specific thrust across the accelerator/nozzle is improved in the MGD solutions over the non-MGD solutions when the load factor is increased and an electron beam type ionization pattern is used. The largest increase in specific thrust is observed in viscous and inviscid flow regimes with a load factor of 1.8 producing 226% and 154% thrust increases, respectively. Flows showing increases in specific thrust with higher load factors also show significant increases in temperature due to the energy interaction term.
DTIC Accession Number
Harrington, Brian H., "Magnetogasdynamic Flow Acceleration in a Scramjet Nozzle" (2004). Theses and Dissertations. 3911.