Linearized theory for compressible unsteady flow is used to treat the problem of a partial-span rectangular control surface, hinged at its leading edge and mounted on a rectangular wing, oscillating in supersonic flow. The notions of the wing-aileron configuration are assumed to consist of vertical translation, pitching, and aileron rotation. The velocity potentials for this configuration are derived as power series in terms of a frequency parameter to the fifth power of the frequency of oscilla-tion. From these potentials closed expressions for section force and moment coefficients at any spanwise location are derived. The section force and moment coefficients are employed in a particular flutter study in which the spanwise position of the aileron is varied.
展开▼
