Annotation
Plasma of transverse-longitudinal direct-current discharge in a supersonic aerodynamic channel with a reverse step is studied experimentally. For deposited powers of 2–3 kW, the gas temperature in the discharge achieves 2000 ± 500 K. The results obtained testify to the applicability of discharge plasma for the ignition of supersonic air-fuel flows.
© 2016 Publisher M.V.Lomonosov Moscow State University
Authors
A.F. Aleksandrov, A.P. Ershov, E.B. Kolesnikov, A.A. Logunov, V.A. Chernikov, V.M. Shibkov
Department of Physical Electronics, Moscow State University, Leninskie gory, Moscow, 119992, Russia
Department of Physical Electronics, Moscow State University, Leninskie gory, Moscow, 119992, Russia
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