Abstract.
The mechanism of the origin of shock oscillations on NACA0012 aerofoils is investigated using a moving grid thin layer Navier Stokes code. The method used to understand the mechanism is to initiate the shock oscillations on an aerofoil by moving the aerofoil from a regime of steady transonic flow into a regime of periodic flow by a change in airflow incidence. The results indicate that the shock induced bubble plays a leading role in the origin of shock oscillations and the trailing edge has an affect on its amplitude.
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Received 1 April 1997 / Accepted 1 December 1997
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Raghunathan, S., Mitchell, R. & Gillan, M. Transonic shock oscillations on NACA0012 aerofoil. Shock Waves 8, 191–202 (1998). https://doi.org/10.1007/s001930050113
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DOI: https://doi.org/10.1007/s001930050113