On the theory of oscillating airfoils at Mach number one (Q1095744)

The theory presented in this paper for flows at \(M=1\) is based on the method of fundamental solutions developed in some previous papers [e.g.: the author, Arch. Mech. 35, 579-590 (1983; Zbl 0559.76051)]. In this theory, the wing is replaced by a continuous distribution of forces. The intensity of this distribution is determined from the boundary conditions. In the case \(M=1\), this is realized by means of a first type Volterra integral equation. Solving this equation we obtain general formulae for the lift and moment coefficients for airfoils of arbitrary form.