In　this　paper,　a　novel　morphing　airfoil　based　on　a　four-corner　simply　supported　bistable　composite　laminated　shell　is　elaborated.　Based　on　the　thin　airfoil　theory,　the　aerodynamic　load　can　be　identified.　Utilizing　the　Hamilton＇s　principle,　dynamic　equations　concerning　the　dynamic　snap-through　and　nonlinear　dynamics　of　the　novel　morphing　airfoil　are　elucidated.　The　inertia,　damping,　restoring　force　and　aerodynamic　load　terms　are　accounted　for　in　the　dynamic　equations.　A　visual　representation　of　the　restoring　force　curve　is　exhibited,　revealing　the　snap-through　and　the　three　equilibrium　states.　A　number　of　quasi-static　locations　are　exhibited　in　the　context　of　the　restoring　force　curve,　generating　a　number　of　related　airfoils.　Thus,　a　graphic　representation　of　the　aerodynamic　coefficients　at　the　pre-snap-through,　snap-through　and　post-snap-through　stages　is　provided.　The　novel　morphing　airfoil　under　minor　disturbances　is　held　constant,　and　its　aerodynamically　controlled　motions　are　characterized　by　the　period　doubling　bifurcation　and　the　1/2-subharmonic　resonance,　which　are　both　depicted　in　a　variety　of　phase　and　frequency　spectrum　diagrams.　Shock　dynamics　under　transient　aerodynamic　excitation　for　large　disturbances　are　detailed,　illuminating　the　limit　cycle　oscillations　and　the　chaotic　snap-through.　The　limit　cycle　oscillations,　the　multiple-period　snap-through　and　the　chaotic　snap-through　are　features　of　the　morphing　airfoil　under　harmonic　excitation.　The　negative　stiffness　system　offered　by　the　bistable　composite　laminated　shell　has　a　significant　influence　on　the　amplitude-frequency　response　curves＇　apparent　softening　nonlinear　effect.　The　development　of　aircraft　morphing　assemblies　can　be　supported　by　this　study.