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Shock tunnel studies on drag reduction of a blunt body using argon plasmajet
, Mahapatra D., Jagadeesh G.
Published in American Institute of Aeronautics and Astronautics Inc.
An experimental investigation of aerodynamic drag reduction by counter flow plasma jet injection from the stagnation region of a hemispherical blunt cylinder model flying at hypersonic Mach numbers are presented. Experiments are carried out in a hypersonic shock tunnel at four different jet- to-pitot pressure ratio and different supply powers. The flow fields around the test model are visualized using high speed schlieren technique. Direct force measurement is also performed using a single component accelerometer balance. The weakly ionized argon plasma jet has an electron temperature around 6400K and electron number density ∼4.9×1015 cm-3. With plasma jet at pressure ratio 72.5 and 1.8 KW supply power the reduction in drag is found to be ∼28% (more than its cold jet counter part) although the plasma jet momentum is less than its cold jet counter part. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.
About the journal
JournalData powered by Typeset47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
PublisherData powered by TypesetAmerican Institute of Aeronautics and Astronautics Inc.
Impact Factor1.868
Open AccessNo
Citation Styleunsrt
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