This paper describes the development of two mathematical methods to analytically model variable camber morphing wing airfoils. The variation in camber is achieved through a combination of droop nose and trailing edge deflections, at the desired hinge locations, from the base airfoil configuration. The surface deflections are achieved in a compliant manner with allowance for variations in the order of morphing. The first method focuses on the preservation of the physical accuracy of morphing by preserving the airfoil shape and camber length of the base airfoil while using camber deflection as the basis for morphing. The second method directly morphs the surface coordinates and allows for the specification of rigid portions at the extreme ends of the airfoil. The results of both codes are directly compared with the results of several published prototypes of morphing wings to cement the accuracy and validity of the two methods arrived at. © 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.