Gust load alleviation by normal microjet

This paper presents an investigation on the capability of gust load alleviation by normal microjet. The numerical method integrates unsteady Reynolds averaged Navier-Stokes (URANS) solutions, structural dynamic equations motion and Field Velocity Method. is verified for responses rigid elastic models. results microjet are validated against experimental previous data. Load control capabilities evaluated 2D NACA0012 airfoil 3D BAH wing with constant momentum coefficients under steady subsonic transonic incoming flow conditions. Thereafter, effects using tested without consideration aeroelasticity. show that has a strong flow. due to jet effect shock strength upper surface. For wing, significant can be shown deployment span near tip. reduction also been observed root away from region. test cases promising approach fast frequency response characteristic. A lift condition achieved adaptively adjusting blowing coefficients.