摘要: The efficacy of a row of streamwise vortex generating jets on enhancing the performance of a 45° swept wing at both the incidence of stall and deep stall is investigated for a range of C_q between 0.003 to 0.02. The NACA 64_3-618 ... 展开 The efficacy of a row of streamwise vortex generating jets on enhancing the performance of a 45° swept wing at both the incidence of stall and deep stall is investigated for a range of C_q between 0.003 to 0.02. The NACA 64_3-618 airfoil wing had a full wing aspect ratio of two and was tested with a streamwise row of vortex generating jets at 70% span for two fixed mass flow rates of 100 and 300 SLPM with a range of Reynolds numbers from 50-500 thousand. Global force measurements were taken to assess the wing performance while surface oil flow visualizations were used to determine the flow structures set up by the active flow control actuation. These experimental methods are used to assess the viability of vortex generating jets at higher Reynolds numbers than previously investigated to unlock new capabilities for active flow control devices. 收起