Amirkabir University of Technology Amirkabir Journal of Mechanical Engineering 2008-6032 52 11 2019 08 05 Effect of Steady Spanwise Blowing on the Aerodynamic Coefficients of a Maneuverable Aircraft Wing Model Effect of Steady Spanwise Blowing on the Aerodynamic Coefficients of a Maneuverable Aircraft Wing Model 3001 3014 3543 10.22060/mej.2019.15222.6063 FA Ahmad Sharafi Aerospace Engineering Faculty, Shahid Sattari Aeronautical University of Science And Technology, Tehran, Iran Matin Al Havaz Department of Mechanical Engineering, KNTU, Tehran, Iran Journal Article 2018 11 01 In this study, the effect of steady spanwise blowing on the aerodynamic coefficients of a maneuverable aircraft wing model has been simulated three dimensionally applying the fluent software. The simulations have been performed at the Mach number of 0.4 and different angles of attack, using unstructured grid and the (k−ω SST) turbulence model. Numerical simulation results showed that the spanwise blowing along the wing leading edge caused a flow along the axis of leading edge vortex and delayed the vortex breakdown until the high angles of attack. As a result, the lift coefficient increases at higher angles of attack, which is directly related to the jet momentum coefficient. By apply blowing, due to the vortex breakdown on the wing surface, drag coefficient is greater in comparison to the no blowing condition until the angle of attack 24 degrees and after this angle, the drag coefficient decreases. Also, drag coefficient decrease is lower at greater jet momentum coefficients. By injecting the flow over the wing, the vortex increases in different longitudinal sections and causes a greater pressure drop on the upper surface of the wing. Also, the greatest amount of pressure in the inner span of the wing and near the edge of the wing attack is observed. In this study, the effect of steady spanwise blowing on the aerodynamic coefficients of a maneuverable aircraft wing model has been simulated three dimensionally applying the fluent software. The simulations have been performed at the Mach number of 0.4 and different angles of attack, using unstructured grid and the (k−ω SST) turbulence model. Numerical simulation results showed that the spanwise blowing along the wing leading edge caused a flow along the axis of leading edge vortex and delayed the vortex breakdown until the high angles of attack. As a result, the lift coefficient increases at higher angles of attack, which is directly related to the jet momentum coefficient. By apply blowing, due to the vortex breakdown on the wing surface, drag coefficient is greater in comparison to the no blowing condition until the angle of attack 24 degrees and after this angle, the drag coefficient decreases. Also, drag coefficient decrease is lower at greater jet momentum coefficients. By injecting the flow over the wing, the vortex increases in different longitudinal sections and causes a greater pressure drop on the upper surface of the wing. Also, the greatest amount of pressure in the inner span of the wing and near the edge of the wing attack is observed. https://mej.aut.ac.ir/article_3543_184d340fcc26ccb596a538a791dec19c.pdf