Assessment of the capability of drag reduction of the shock control device 'SC bump' on airfoil flows and application aspects on wings

摘要

Based on studies abput various concepts to control the shock boundary layer interference the adaptive SC bump seems to be the most efficient shock control device to reduce drag in the off-design condition.The influence of the bump geometry on the drag behaviour is numerically investigated using a DA laminar airfoil and verified by airfoil experiments in the ONERA wind tunnel Ta.In spites of encouraging experimental results in drag reduction with a wing-body configuration equipped with a fixed bump in 3D flow condition,the practical application on wings is not solved due to design and integration problems.