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In the sixth part of this series, we continue our study started in the previous article, i.e., we present the basis of the method for calculating the unsteady airforces on oscillating non-lifting bodies. The method proposed here is a panel one. As it is proved in the previous paper, the potential and velocity induced by a constant source planar panel is composed of two kinds of terms: some of themthe steady terms, can be expressed by the elementary functions; other termsthe unsteady terms cannot and should be calculated numerically. The present paper illustrates how the method proposed here can be used in conjunction with the preceding results.

Aerodynamic Interference between Oscillating Lifting Surfaces and Fuselage. Part 6: A Panel Method for Non-Lifting Bodies Oscillating in Subsonic Flow