Abstract:
A method of obtaining numerical values of generalised airforces on a thin wing oscillating harmonically in subsonic flow is described. It is assumed that the linearised equations of potential flow are valid. The essence of the method is the approximate solution, by collocation, of the integral equation relating the loading distribution and upwash on the wing and the use of the loading distribution so determined to calculate the generalised forces on the wing and control surfaces at general frequencies of oscillation. The procedure has been programmed in autocode for the Ferranti Mercury Computer and.is available as programme R.A.E.161A. A modification is programme R.A.E.263A for determining the loading distribution over the wing.
