Accession Number:

ADA426653

Title:

Magnetogasdynamic Flow Acceleration in a Scramjet Nozzle

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

Report Date:

2004-06-01

Pagination or Media Count:

83.0

Abstract:

The effect of magnetogasdynamic MGD interactions on flow acceleration and thrust in a scramjet acceleratornozzle 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 acceleratornozzle 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.

Subject Categories:

  • Plasma Physics and Magnetohydrodynamics
  • Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE