Closed-loop separation control using oscillatory flow excitation

Brian G Allan, Jer-Nan Juang, David L Raney, Avi Seifert, Latunia G Pack, Donald E Brown

Research output: Book/ReportReport


Design and implementation of a digital feedback controller for a flow control experiment was performed. The experiment was conducted in a cryogenic pressurized wind tunnel on a generic separated configuration at a chord Reynolds number of 16 million and a Mach number of 0.25. The model simulates the upper surface of a 20% thick airfoil at zero angle-of-attack. A moderate favorable pressure gradient, up to 55% of the chord, is followed by a severe adverse pressure gradient which is relaxed towards the trailing edge. The turbulent separation bubble, behind the adverse pressure gradient, is then reduced by introducing oscillatory flow excitation just upstream of the point of flow separation. The degree of reduction in the separation region can be controlled by the amplitude of the oscillatory excitation. A feedback controller was designed to track a given trajectory for the desired degree of flow reattachment and to improve the transient behavior of the flow system. Closed-loop experiments demonstrated that the feedback controller was able to track step input commands and improve the transient behavior of the open-loop response.
Original languageEnglish
Place of PublicationHampton (VA)
PublisherNational Aeronautics and Space Administration
Number of pages23
StatePublished - 1 Aug 2000


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