A combination of time-resolved particle image velocimetry and unsteady pressure measurements is used to analyze the unsteady flow over an aeroelastic supercritical BAC 3-11 transport-type wing configuration in subtransonic flow. The dynamic interaction between the shock wave and turbulent separation is the essential feature of the unsteady flow causing a distinct self-induced oscillation of both the wing structure and the flowfield. Results from wind-tunnel experiments with a variation of the freestream Mach number at Reynolds numbers sigma(107 m-1 are analyzed regarding the origin and nature of the unsteady shock wave-boundary layer interaction. Time-resolved particle image velocimetry results are presented for a flow case with a weak shock and incipient separation as well as for a case with medium shock strength and full-scale trailing-edge separation. The visualization of the flowfield, which is time-resolved regarding the shock wave oscillation, demonstrates the two-fold nature of the shock wave-boundary layer interaction, on the one hand being the origin of aerodynamic unsteadiness at marginally separated flow, on the other hand damping the fluctuation level at full-scale separation.
Time-resolved particle image velocimetry of unsteady shock wave-boundary layer interaction
Zeitlich aufgelöste Teilchenabbildgeschwindigkeitsmessung der instationären Wechselwirkung zwischen Stoßwelle und Grenzschicht
AIAA Journal ; 49 , 1 ; 195-204
2011
10 Seiten, 12 Bilder, 40 Quellen
Article (Journal)
English
Time-Resolved Particle Image Velocimetry of Unsteady Shock Wave-Boundary Layer Interaction
Online Contents | 2011
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