Design and Development of Aircraft Wing Using Various Flow Control Methods
摘要
The paper aims to estimate the potency of the active flow control technique by comparing different injection suction systems on an aerofoil, with the objective of enhancing its aerodynamic performance. Various injection suction mechanisms are analysed and compared with a baseline configuration by means of numerical investigations at the flow Reynold number 5.1 × 105. The vertical injection suction system manifests significantly better results, improving the stall angle by 33%, and increasing the lift coefficient by up to 51% as compared to both the baseline and traditional co-flow jet aerofoils. This research is an effort directed to identifying and comparing suitable injection suction methods for enhancement of aerofoil performance. The novelty and superiority of the vertical injection suction system as an active flow control method need not be over-emphasized as it exhibits comparatively more promising results. Additionally, the proposed method is viable and will suffice for various applications in subsonic aircraft wings with advantages such as reduced pumping power requirements compared to the conventional co-flow jet method.