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

作　　者：T.H.New S.Mandra 

机构地区：[1]School of Mechanical and Aerospace Engineering,Nanyang Technological University,50 Nanyang Avenue,Singapore 639798,Singapore [2]Institut für Fluiddynamik,ETH Zürich,Sonneggstrasse 3,Zürich 8092,Switzerland

出　　处：《Advances in Aerodynamics》2024年第1期160-178,共19页空气动力学进展(英文)

基　　金：the support for the research project by ETH Zurich;Nanyang Technological University, Singapore。

摘　　要：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=1.8×10^(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.

关 键 词：Leading-edge tubercles Finite wings Vortex systems Yaw Numerical simulation 

分 类 号：O35[理学—流体力学]