This study investigates the potential of Fish Bone Morphing(FBM)technology for enhancing the aerodynamic performance of aerofoils.FBM is a bio-inspired concept that incorporates flexible structural elements to facilit...This study investigates the potential of Fish Bone Morphing(FBM)technology for enhancing the aerodynamic performance of aerofoils.FBM is a bio-inspired concept that incorporates flexible structural elements to facilitate morphing of the aerofoil shape in response to varying flight conditions.The NACA 2412 aerofoil is chosen for its camber adaptability,and CFD simulations are employed to assess the efficacy of FBM integration.The k-ω SST turbulence model is adopted for its ability to combine the strengths of the k-ω and k-ε models.The investigation encompasses a systematic exploration of geometric configurations,including trailing edge deflection at various chord lengths(0.6c,0.65c,0.70c,0.75c,and 0.80c)and deflection angles(4°,8°,and 12°).The results reveal that FBM aerofoils exhibit a consistent increase in maximum lift coefficient compared to conventional aerofoils across all deflection points and angles.Additionally,improvements in lift-todrag ratio are observed.Furthermore,the stalling angle remains unaffected by deflection point variations,while deflection angle increments lead to corresponding increases in maximum lift coefficient.The morphing aerofoil with a 0.60c deflection point demonstrates themost significant enhancement in maximum lift coefficient,achieving a 13% increase at a 12°deflection angle.These findings establish the aerodynamic efficiency of FBM aerofoils,characterized by superior lift-to-drag ratios and increased maximum lift coefficients.展开更多
文摘This study investigates the potential of Fish Bone Morphing(FBM)technology for enhancing the aerodynamic performance of aerofoils.FBM is a bio-inspired concept that incorporates flexible structural elements to facilitate morphing of the aerofoil shape in response to varying flight conditions.The NACA 2412 aerofoil is chosen for its camber adaptability,and CFD simulations are employed to assess the efficacy of FBM integration.The k-ω SST turbulence model is adopted for its ability to combine the strengths of the k-ω and k-ε models.The investigation encompasses a systematic exploration of geometric configurations,including trailing edge deflection at various chord lengths(0.6c,0.65c,0.70c,0.75c,and 0.80c)and deflection angles(4°,8°,and 12°).The results reveal that FBM aerofoils exhibit a consistent increase in maximum lift coefficient compared to conventional aerofoils across all deflection points and angles.Additionally,improvements in lift-todrag ratio are observed.Furthermore,the stalling angle remains unaffected by deflection point variations,while deflection angle increments lead to corresponding increases in maximum lift coefficient.The morphing aerofoil with a 0.60c deflection point demonstrates themost significant enhancement in maximum lift coefficient,achieving a 13% increase at a 12°deflection angle.These findings establish the aerodynamic efficiency of FBM aerofoils,characterized by superior lift-to-drag ratios and increased maximum lift coefficients.
