On the effects of non-zero yaw on leading-edge tubercled wings

Steady-state numerical simulations were conducted to capture the aerodynamic characteristics and flow patterns resulting from a tubercled and non-tubercled wing subjected to various combined pitch and yaw conditions at $$Re=1.8 \times 10^{5}$$ . Pitch angle ranged from $$0^{\circ }$$ to $$25^{\circ }$$ , while two different yaw angles of $$10^{\circ }$$ and $$30^{\circ }$$ were used. Results show that $$10^{\circ }$$ yaw angle does not impact upon the lift and drag characteristics significantly, while a $$30^{\circ }$$ yaw angle leads to substantial lift and drag losses. Additionally, the tubercled wing continues to confer favourable stall-mitigating characteristics even for the larger yaw angle. Finally, despite skewing the flow structures significantly, the $$30^{\circ }$$ yaw angle also reduces the formations of bi-periodic flow structures, flow separations and recirculating regions along the leading-edge tubercles, suggesting potentially better flow stability and controllability. • Steady-state numerical study is conducted on NACA 634021 baseline and tubercled wings • Two yaw angles of $$10^{\circ }$$ and $$30^{\circ }$$ are used together with pitch angles from $$0^{\circ }$$ to $$25^{\circ }$$ • Results show $$10^{\circ }$$ yaw angle has minimal impact on the lift and drag characteristics, while $$30^{\circ }$$ yaw angle reduces both lift and drag levels significantly • Larger yaw angle leads to more skewed flows, as well as reduced flow separations and recirculating regions • Larger yaw angle also suppresses bi-periodic flow behaviour in tubercled wings, suggesting better flow stability and controllability