ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Experimental investigation on supersonic boundary layer separation control by plasma aerodynamic actuation
Received date: 2014-03-18
Revised date: 2014-04-16
Online published: 2014-04-21
Supported by
National Natural Science Foundation of China (51336011, 51276197, 51207169)
Plasma aerodynamic actuation and supersonic flow interaction has become the focus of researches. There is a wide range of universal phenomenon of shock wave and boundary layer interaction in supersonic aircraft. Experimental investigation on boundary layer separation induced by ramp and impinging shock wave are performing in supersonic flow by plasma aerodynamic actuation. Through schlieren imaging and wall static pressure results, plasma-shock wave interaction and shock-boundary layer interaction mechanism are studied. Experimental results show that the millisecond plasma actuation can make the shock wave induced by the ramp forward and enlarge the separation area. At the same time, the intensity of shock wave induced by the ramp is weakened. The main control mechanism are Joule heating effect. The microsecond plasma actuation can control the boundary layer separation induced by the impinging shock wave and reduce the separation area but the overall pressure reduced. The main control mechanism is Joule heating effect and impact effect based on experimental results.
Key words： supersonic; shock wave; boundary layer; plasma; flow control
SUN Quan , CUI Wei , CHENG Bangqin , JIN Di , LI Jun . Experimental investigation on supersonic boundary layer separation control by plasma aerodynamic actuation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(2) : 501 -509 . DOI: 10.7527/S1000-6893.2014.0062
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