A previously published method for the calculation of aerodynamic forces on oscillating wings with partial-span control-surfaces in subsonic flow by using polar integration variables has been generalized and programmed in Fortran. The program can treat combinations of up to 10 trapezoidal surfaces with several control-surfaces and tabs. The input data for the deflection modes may consist of measured values. These are treated by a subprogram that fits a function with suitable edge characteristics to the data for each mode. Numerical results are given for several configurations. Comparisons for simple modes with results of other methods show close agreement in most cases.
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