The paper employs arbitrary airfoil blade design procedures of turbomachinery to design a transonic wide-chord fan with forward-swept and back-swept blades.In the process of designing

the radial distributions of parameters(such as total pressure ratio

maximum relative thickness and thickness of leading and trailing edges of blade and so on

camber and maximum thickness as a fraction of chord) are adjusted

so that shock intension of blade tip is weakened

the loss of shock is debased

the conflict of high relative Mach number with low loss and high efficiency is overcome.Numerical simulation of core and bypass indicates that

the fan has a higher efficiency over a wider range and better stall margin.