5- 2-1 General Remarks

Now that some experimental results have been given, the theory of flow over fuselages will be presented. Fuselage theory can be established, similar to profile theory, by two different approaches.

The first approach consists of the establishment of exact solutions of the three-dimensional potential equation, which can be done successfully in only a few cases. The second approach is the so-called method of singularities, in which the flow pattern about the fuselage is formed by arranging sources, sinks and, if necessary,
dipoles on the fuselage axis. This procedure is fairly simple for bodies of revolution (see von Karman [54] and Keune and Burg [26]). An extention of this method for the computation of the flow over fuselages consists of arranging ring-shaped source distributions on the body surface (see Lotz [34], Riegels [32], and Hess [IB]). By this method, body shapes can be treated whose cross sections deviate somewhat from circles.

First, the fuselage in axial flow will be discussed, then the fuselage in oblique flow.

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