Mahapatra, D and Sriram, R and Jagadeesh, G (2008) Effect of counterflow argon plasma jet on aerodynamic drag of a blunt body at hypersonic Mach numbers. In: Aeronautical Journal, 112 (1137). pp. 683-687.Full text not available from this repository. (Request a copy)
An experimental investigation of aerodynamic drag reduction by counter now 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 ratios namely 15.3, 24-52, 72.5 and 96.67 and three supply powers, namely 1.8KW, 2.7KW and 3.6KW. The flow fields around the test model are visualised using high speed schlieren technique. Direct force measurement is also performed using a single component accelerometer balance. The weakly ionised argon plasma jet has ill electron temperature around 6,400K and electron number density similar to 1.64 x 10(15)cm(-3). With plasma jet at pressure ratio 72.5 and 1.8KW supply power the reduction in drag is found to be similar to 28% (more than its cold jet counter part) although the plasma jet momentum is less than its cold jet counter part.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to Royal Aeronautical Society.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||30 Apr 2009 05:18|
|Last Modified:||30 Apr 2009 05:18|
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