Abstract
An experimental scramjet driven MHD generator developed under the US AFRL’s Hypersonic Vehicle Electric Power System (HVEPS) program as described in Reference 1, has been numerically simulated and analyzed using a three dimensional MHD generator computer code. The three dimensional simulations very good agreement is obtained between the experimental and numerical results in the active MHD region when a scalar electrical conductivity deficit of 81.3% of ideal is imposed on the electrophysical properties. The major power performance loss mechanism identified in the three dimensional simulation is relatively large near electrode voltage drops on the order of 100 Volts with a ratio to the induced MHD voltage from 0.3 to 0.4. The three dimensional flow simulation arrived at by the simulation well characterizes that typical to a scramjet driven MHD generator complete with the embedded shock train. The analysis could not reproduce the very large electrical loss in end power take-off regions as was exhibited in the experimentally measured voltage distributions and detailed calculations of localized phenomena associated with current transport in these end regions is required.
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