Abstract
In this paper the boundary integral equation method is applied to the subsonic flow in the presence of three-dimensional bodies or of wings. The integral equation is obtained by the aid of a source distribution on the body surface. The equation discretization is obtained via a collocation method using triangular elements. Numerical tests are performed for the case of the sphere in incompressible fluid (in this case the exact solution is known). Numerical results are also given for the ellipsoid at 0° and 10° incidence for various values of the Mach numberM. The method allows also to consider lifting wings. Numerical determinations are performed for a wing whose section is a NACA64A-008 airfoil.
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