A numerical method to obtain a complete solution of the dynamic response of a variable swept wing aircraft in the course of changing the sweep angle is presented. Both aerodynamic and trajectory computations are included. A method for calculating the unsteady aerodynamic characteristics of wing/tail combinations at subsonic speeds under varying sweep backs is developed. The method uses a potential flow model consisting of discrete unsteady vortex rings distributed over the wing and tail surfaces. A set of complete equations for flight dynamics in the main body axes is formed with a deformable system dynamics. The time history method is used to calculate the aerodynamic characteristics and the aircraft responses. All aerodynamic and flight dynamic parameters during the whole course of varying the sweep back have been obtained and such influences as various control rules, flight Mach number, etc., on aircraft response during that vaiation have been satisfactorily analyzed. Some computation examples and response analyses are presented that are useful for studying the flight stability, maneuverability, and safety of wing sweep change at low altitudes.
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An et al. (1988) studied this question.