Abstract: In this paper,a numerical method based on the nonlinear potential equation containing all the quadratic terms for computing the nonlinear aerodynamic loads on wings with sharp edge separations at large angles of attack in subcritical near-sonic flows is presented. A local linearization assumption is imposed in this method. Through an iteration procedure, the Problem with two sources of noalinearities, namely, a boundary-oriented （separated flow roll-up） and equation-oriented nonlinearity, is treated successfully. Numerical results are compared with experimental data aad are found to be in good agreement. In addition, the method is also applicable to complex wing planforms. By comparing with the finite difference methods and the method based on the integral approach, the present method appears to be economic.