Abstract
The laminar-turbulent transition on an airfoil can be delayed by active control of Tollmien Schlichting (TS) waves in an early stage of a transitional boundary layer using the superposition principle. The present study compares two sensor types regarding their ability to detect TS-waves at various Mach and Reynolds numbers on a transonic profile. Surface hot wire and the surface hot film sensor signals are used to characterize the flow field on a transonic airfoil model. The results are applied as basis for the active wave control experiments at a chordlength Reynolds number of Re c = 3.9 ·106 (c = 1m) at M ∞ = 0.50 and an angle of attack α = − 1°. Cancellation results of 44% amplitude are presented for a voice coil driven actuator.
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Erdmann, R., Leuckert, J., Rosemann, H., Nitsche, W. (2013). Active Tollmien Schlichting Wave Control with a Membrane Actuator in Compressible Flows. In: Dillmann, A., Heller, G., Kreplin, HP., Nitsche, W., Peltzer, I. (eds) New Results in Numerical and Experimental Fluid Mechanics VIII. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 121. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-35680-3_31
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DOI: https://doi.org/10.1007/978-3-642-35680-3_31
Publisher Name: Springer, Berlin, Heidelberg
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