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Steady subsonic flow around finite-thickness wings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kuo, C. C. Morino, L. |
| Copyright Year | 1975 |
| Description | The general method for analyzing steady subsonic potential aerodynamic flow around a lifting body having arbitrary shape is presented. By using the Green function method, an integral representation for the potential is obtained. Under small perturbation assumption, the potential at any point, P, in the field depends only upon the values of the potential and its normal derivative on the surface of the body. Hence if the point P approaches the surface of the body, the representation reduces to an integral equation relating the potential and its normal derivative (which is known from the boundary conditions) on the surface. The question of uniqueness is examined and it is shown that, for thin wings, the operator becomes singular as the thickness approaches zero. This fact may yield numerical problems for very thin wings. However, numerical results obtained for a rectangular wing in subsonic flow show that these problems do not appear even for thickness ratio tau = .001. Comparison with existing results shows that the proposed method is at least as fast and accurate as the lifting surface theories. |
| File Size | 2165732 |
| Page Count | 90 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760004926 |
| Archival Resource Key | ark:/13960/t6c29p71v |
| Language | English |
| Publisher Date | 1975-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Perturbation Theory Lifting Bodies Subsonic Flow Rectangular Wings Thin Wings Potential Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
