Flow Control by Pulsed Jet in a Curved S -Duct: A Spectral Analysis
Flow Control by Pulsed Jet in a Curved S -Duct: A Spectral Analysis
This paper presents an experiment of flow control by supersonic pulsed jets in a very aggressive S-duct typical of modern fighter aircraft engine inlet ducts. The Mach number in the aerodynamic interface plane ranges from 0.2 to 0.4, which is realistic from an application point of view. It was shown that, with continuous blowing, the flow could be fully reattached. The sensitivity of the distortion coefficient to the jet frequency was also clearly evidenced. Surprisingly, it is recommended to avoid actuating the jets at the natural frequencies present in the separated zone of the uncontrolled flow. Besides, it is observed that pulsed jets actuation increases the unsteady flow distortion. Furthermore, in the uncontrolled flow, a lateral movement of the structures associated with high total pressure losses in the aerodynamic interface plane was highlighted. Presented as Paper 2012-3250 at the 6th AIAA Flow Control Conference, New Orleans, LA, 25-28 June 2012
Dokumentinformationen
Flow Control by Pulsed Jet in a Curved S -Duct: A Spectral Analysis
AIAA journal ; 53 , 10
2015
Aufsatz (Zeitschrift)
Englisch
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