Active control of flow noise sources in turbulent boundary layer on a flat-plate using piezoelectric bimorph film
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The piezoelectric bimorph film, which, as an actuator, can generate more effective displacement than the usual PVDF film, is used to control the turbulent boundary-layer flow. The change of wall pressures inside the turbulent boundary layer is observed by using the multi-channel microphone array flush-mounted on the surface when actuation at the non-dimensional frequency f b + =0.008 and 0.028 is applied to the turbulent boundary layer. The wall pressure characteristics by the actuation to produce local displacement are more dominantly influenced by the size of the actuator module than the actuation frequency. The movement of large-scale turbulent structures to the upper layer is found to be the main mechanism of the reduction in the wallpressure energy spectrum when the 700v/uτ-long bimorph film is periodically actuated at the non-dimensional frequency f b + =0.008 and 0.028. The biomorph actuator is triggered with the time delay for the active forcing at a single frequency when a 1/8″ pressuretype, pin-holed microphone sensor detects the large-amplitude pressure event by the turbulent spot. The wall-pressure energy in the late-transitional boundary layer is partially reduced near the convection wavenumber by the open-loop control based on the large amplitude event.
Key WordsFlow Control Piezoelectric Bimorph Wavenumber-Frequency Spectrum
Normalized streamwise length (≡ uτΔx/v)
Normalized spanwise length (≡ uτΔz/v)
Mean bursting frequency (≡ fv/u τ 2
Non-dimensional pin-hole diameter (≡ uτd/v)
Reynolds number based on momentum thickness
Streamwise wavenumber (rad/m)
Mean wall shear-stress
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- Gad-el-Hak, M., 2000, Flow Control, Cambridge University Press.Google Scholar
- Landahl, M. T., 1975, “Wave Mechanics of Boundary Layer Turbulence Layer,”J.A.S.A., Vol. 57, pp. 824–831Google Scholar
- Lee, S. and Kim, H.-J., 1999, “Experimental Study on Wall Pressure Fluctuations in the Turbulent Boundary Layer on a Flat-Plate,”J. KSME, Part B, 23, No. 6, pp. 722–733.(in Korean)Google Scholar
- Wehrmann, O. H., 1967, “Self-Adjusting Feedback Loop for Mechanical Systems to Influence Flow in Transition. Part I,” Boeing Scientific Research Lab., Document D1-82-0632.Google Scholar