Study of Shock-Wave Boundary-Layer Interaction Control Using an Array of Steady Micro-Jet Actuators

An experimental investigation was conducted to control the amplitude of shock unsteadiness associated with the interaction induced by a (i) 24o compression corner and, (ii) a cylindrical obstruction on a flat plate in a Mach 2 flow. The control was applied in the form of an array of steady micro air-jets of different configurations with variation in pitch angle (β) and skew angle (α) of the jets. The overall flow interaction gets modified for all control configurations and shows a reduction in both separation- and bow-shock strengths and in triple-point height. A significant reduction in σmax /Pw value is also observed in the intermittent region of separation for each case. On the other hand, pitching or skewing the jets to 45o or both reduces the obstruction component considerably that initially, at lower control pressure, shows lower effectiveness (relative to 90o pitched jets). But at higher control pressure, the effectiveness of these configurations continues to increase unlike the 90o pitched jets