![]() Melling A (1986) Seeding gas flows for laser anemometry. Lee BHK, Murty H, Jiang H (1994) Role of kutta waves on oscillatory shock motion on an airfoil. Lee BHK (2001) Self-sustained shock oscillations on airfoils at transonic speeds. Hartmann A, Steimle PC, Klaas M, Schröder W (2011) Time-resolved particle-image velocimetry of unsteady shock wave-boundary layer interaction. Guntermann P (1992) Entwicklung eines Profilmodells mit variabler Geometrie zur Untersuchung des Transitions-verhaltens in kompressibler Unterschallströmung. ![]() Green JE (1970) Interactions between shock waves and turbulent boundary layers. Geissler W (2003) Numerical study of buffet and transonic flutter on the NLR 7301 airfoil. AGARDograph 280:90–108Įlsinga GE, van Oudheusden BW, Scarano F (2005) Evaluation of aero-optical distortion effects in PIV. Progr Aerosp Sci 22:209–280ĭélery J, Marvin JG (1986) Shock-wave boundary layer interactions. AIAA J 43(7):1556–1566ĭélery JM (1985) Shock wave/turbulent boundary layer interaction and its control. ONERA-TP-2006-165ĭeck S (2005) Numerical simulation of transonic buffet over a supercritical airfoil. In: Proceedings of the 7th ONERA-DLR aerospace symposium ODAS 2006, Toulouse, France. 4īrunet V, Deck S, Jacquin L, Molton P (2006) Transonic buffet investigations using experimental and des techniques. In: Reynolds number effects in transonic flow. DFVLR-FB, pp 85–62īinion TW (1988) Potentials for pseudo-reynolds number effects. Ann Rev Fluid Mech 12:103–138Īmecke J (1985) Direkte Berechnung von Wandinterferenzen und Wandadaption bei zweidimensionaler Strömung in Windkanälen mit geschlossenen Wänden. Thereby, the pulsation of the separation could be determined to be a reaction to the shock motion and not vice versa.Īdamson TC Jr, Messiter AF (1980) Analysis of two-dimensional interactions between shock waves and boundary layers. The results show that such upstream-propagating disturbances could be identified to be responsible for the upstream displacement of the shock wave and that the feedback loop is formed by a pulsating separation of the boundary layer dependent on the shock position and the sound pressure level at the shock position. The other two buffet flows have been intentionally influenced by an artificial acoustic source installed downstream of the test section to investigate the behavior of the interaction to upstream-propagating disturbances generated by a defined source of noise. One flow exhibits a sinusoidal streamwise oscillation of the shock wave only due to an acoustic feedback loop formed by the shock wave and the trailing-edge noise. Therefore, the TR-SPIV results are analyzed for three buffet flows. ![]() Results from wind-tunnel experiments with a variation of the freestream Mach number at Reynolds numbers ranging from 2.55 to 2.79 × 10 6 are analyzed regarding the origin and nature of the unsteady shock–boundary layer interaction. The dynamic shock wave–boundary layer interaction is one of the most essential features of this unsteady flow causing a distinct oscillation of the flow field. Time-resolved stereo particle-image velocimetry (TR-SPIV) and unsteady pressure measurements are used to analyze the unsteady flow over a supercritical DRA-2303 airfoil in transonic flow.
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