Application of the boundary integral equation methods to subsonic flow past bodies and wings. (English) Zbl 0732.76065
Summary: 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 \(0\circ\) and 10\(\circ\) incidence for various values of the Mach number M. The method allows also to consider lifting wings. Numerical determination are performed for a wing whose section is a NACA- 64A-008 airfoil.
MSC:
| 76M25 | Other numerical methods (fluid mechanics) (MSC2010) |
| 76G25 | General aerodynamics and subsonic flows |
| 65R20 | Numerical methods for integral equations |
| 65N35 | Spectral, collocation and related methods for boundary value problems involving PDEs |
Keywords:
boundary integral equation method; subsonic flow; source distribution; collocation method; triangular elements; NACA-64A-008 airfoilReferences:
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| [3] | Hess, J. L., Smith, A. M. Q.: Calculation of nonlifting potential flow about arbitrary threedimensional bodies. J. Ship Res., September 1964. |
| [4] | Dragos, L., Dinu, A.: Application of the boundary element method to the thin airfoil theory. AIAA J. (to appear). · Zbl 0815.76047 |
| [5] | Dragos, L.: Boundary element methods in the theory of thin airfoils. Rev. Roum. Math. Pures et Appl.34, 523-531 (1989). · Zbl 0676.76056 |
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