Investigation on the effect of leading edge tubercles of sweptback wing at low reynolds number

摘要: Aerodynamic efficiency of an airplane wing can be improved either by increasing its lift generation tendency or reducing the drag. Recently, Bio-inspired designs have been received greater attention for geometric modifications wings. One bio-inspired contains sinusoidal Humpback Whale (HW) tubercles, i.e., protuberances exist at leading edge (LE). The tubercles excellent flow control characteristics low Reynolds numbers. present work describes about effect on swept back performance various Angle Attack (AoA). NACA 0015 and 4415 airfoils are used design with sweep angle 30°. modified wings (HUMP A, HUMP B, B) designed two amplitude to wavelength ratios (η ) 0.1 & 0.24 analysis. It is a novel effort analyze tubercle vortices along span that induce additional energy especially, behind peak trough region. Subsequently, Co-efficient Lift (C L ), Drag D boundary layer pressure gradients also predicted baseline (smooth LE) models in pre post-stall regimes. was observed increase enhanced C /C ratio pre-stall AoA Interestingly, separation region centerline formation Laminar Separation Bubbles (LSB) were asymmetric because sweep.