Abstract:
The method developed by C. E. Watkins and J. H. Berman in N.A.C.A. Report 1099 and N.A.C.A. Technical Note 3009 is used to obtain the velocity potential on a triangular (or related) wing with subsonic leading edges oscillating in a supersonic flow. A symmetric mode of oscillation is considered which is represented by a polynomial expression in the co-ordinates of the points of the wing. This polynomial expression is of higher degree than those of the above two papers. The results enable the first few terms of a power series in frequency for the velocity potential to be obtained.
