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 R e = 1.8 × 10 5 . Pitch angle ranged from 0 ∘ to 25 ∘ , while two different yaw angles of 10 ∘ and 30 ∘ were used. Results show that 10 ∘ yaw angle does not impact upon the lift and drag characteristics significantly, while a 30 ∘ 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 ∘ 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. Highlights • Steady-state numerical study is conducted on NACA 634021 baseline and tubercled wings • Two yaw angles of 10 ∘ and 30 ∘ are used together with pitch angles from 0 ∘ to 25 ∘ • Results show 10 ∘ yaw angle has minimal impact on the lift and drag characteristics, while 30 ∘ 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