Summary
The present work reports the overall research activity conducted by CIRA within the EUROSHOCK II project (Task 2). The aim was to improve aerodynamic airfoil performance (drag reduction and buffet onset) using shock and boundary-layer active control techniques. The numerical flow simulation has been performed using the computational capabilities developed within EUROSHOCK (I) and the results have been validated through comparison with the experiments performed in Task 3. The method is based on a viscous-inviscid coupling technique and on different models for the calculation of the transpiration velocity on the airfoil surface which have been implemented and tested during the first phase of the activity. The control techniques which have been applied are: bumps, discrete slot suction, passive and active ventilation through perforated plates, and their combinations. A new concept of “pneumatic” bump, based on distributed blowing, has been tested and compared with the classical contour bump. Tests performed on both, laminar and turbulent airfoils have confirmed the results of the present numerical analyses.
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Dima, C., de Matteis, P. (2002). Numerical Investigation of Active Shock Wave and Boundary-Layer Control on Airfoils and Sheared Wings. In: Stanewsky, E., Délery, J., Fulker, J., de Matteis, P. (eds) Drag Reduction by Shock and Boundary Layer Control. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 80. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45856-2_6
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