Shock oscillations on biconvex aerofoils

The mechanism of the origin of shock oscillations on an 18% thick biconvex aerofoil is investigated using a thin-layer Navier-Stokes code. The approac h used in this study is to initiate shock oscillations on an aerofoil in tr ansonic Row by moving the aerofoil from a regime of non-periodic flow to a regime where periodic flow does occur by withdrawal of a trailing-edge spli tter plate. The results indicate that the shock induced separation plays a leading role in the origin of shock oscillations. (C) Elsevier, Paris.