Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance

This paper presents an unsteady flow analysis of a 3D wing with morphing trailing edge flap (TEF) and seamless side-edge transition between the morphed static parts by introducing parametrization method. First, steady Reynolds-averaged Navier–Stokes (RANS) statically TEF is performed results are compared both baseline clean traditional hinged configuration at Reynolds number 0.7 × 106 for range angles attack (AoA), from 4° to 15°. study extends some previous published work examining inherent effects due presence transition. It found that in pre-stall regime, produces maximum 22% higher lift near constant drag reduction 25% wing, resulting up 40% enhancement aerodynamic efficiency (i.e., lift/drag ratio). Second, dynamically provide further insights into dynamic forces during motions three pre-defined frequencies 4 Hz, 6 8 respectively. Results have shown initially large overshoot coefficient observed induced wing; proportional frequency which indicates need account design phase wing.