Abstract
The piecewise continuous-kernel function method is applied to wings with geometrical discontinuities. These discontinuities include leading-edge extension, leading-edge and trailing-edge control surface rotations, and gaps of various sizes around the trailing-edge control surface. In all cases, the results obtained are compared with those obtained by the vortex- or doublet-lattice methods. These results indicate the effectiveness of the present method and the inability of the lattice methods to produce results with reasonable accuracy for leading- or trailing-edge control surfaces when gaps exist about them.
| Original language | English |
|---|---|
| Pages (from-to) | 356-363 |
| Number of pages | 8 |
| Journal | Journal of Aircraft |
| Volume | 18 |
| Issue number | 5 |
| DOIs | |
| State | Published - May 1981 |
| Externally published | Yes |