The reduction in aerodynamic drag by injecting a gaseous jet from the nose of a blunt body into a supersonic stream is investigated numerically. The penetration of the jet into the supersonic flow modifies the shock structure around the body and creates a low pressure recirculation zone, thereby decreasing the wave drag significantly. Combining various theoretical estimates of different flow features and numerical simulations, we identify a universal parameter, called the jet to freestream momentum ratio (RmA), which uniquely governs the drag on the blunt body. The momentum ratio fundamentally decides the penetration of the jet as well as the extent of low pressure envelope around the body. In addition, various influencing parameters reported in the literature are reviewed for different steady jet flow conditions. Furthermore, their limitations in regulating the flowfield are explained by correlating the facts with the jet to freestream momentum ratio. We perform the simulations for various combinations of physical and flow parameters of the jet and the freestream to show a universal dependence of drag on the momentum ratio.
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March 2020
Research Article|
March 20 2020
Universal scaling parameter for a counter jet drag reduction technique in supersonic flows Available to Purchase
Siddesh Desai
;
Siddesh Desai
a)
1
Department of Computational Science, Kobe University
, Kobe 6578501, Japan
2
Department of Mechanical Engineering, Indian Institute of Technology Guwahati
, Guwahati 781039, India
a)Author to whom correspondence should be addressed: [email protected]
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Vishnu Prakash K;
Vishnu Prakash K
2
Department of Mechanical Engineering, Indian Institute of Technology Guwahati
, Guwahati 781039, India
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Vinayak Kulkarni;
Vinayak Kulkarni
2
Department of Mechanical Engineering, Indian Institute of Technology Guwahati
, Guwahati 781039, India
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Hrishikesh Gadgil
Hrishikesh Gadgil
3
Department of Aerospace Engineering, Indian Institute of Technology Bombay
, Mumbai 400076, India
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Siddesh Desai
1,2,a)
Vishnu Prakash K
2
Vinayak Kulkarni
2
Hrishikesh Gadgil
3
1
Department of Computational Science, Kobe University
, Kobe 6578501, Japan
2
Department of Mechanical Engineering, Indian Institute of Technology Guwahati
, Guwahati 781039, India
3
Department of Aerospace Engineering, Indian Institute of Technology Bombay
, Mumbai 400076, India
a)Author to whom correspondence should be addressed: [email protected]
Physics of Fluids 32, 036105 (2020)
Article history
Received:
November 25 2019
Accepted:
March 02 2020
Citation
Siddesh Desai, Vishnu Prakash K, Vinayak Kulkarni, Hrishikesh Gadgil; Universal scaling parameter for a counter jet drag reduction technique in supersonic flows. Physics of Fluids 1 March 2020; 32 (3): 036105. https://doi.org/10.1063/1.5140029
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