| タイトル | An analytical procedure for computing smooth transitions between two specified cross sections with applications to blended wing body configuration |
| 本文（外部サイト） | http://hdl.handle.net/2060/19820017317 |
| 著者（英） | Barger, R. L. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1982-05-01 |
| 言語 | eng |
| 内容記述 | An analytical procedure is described for designing smooth transition surfaces for blended wing-body configurations. Starting from two specified cross section shapes, the procedure generates a gradual transition from one cross section shape to the other as an analytic blend of the two shapes. The method utilizes a conformal mapping, with subsequent translation and scaling, to transform the specified and shapes to curves that can be combined more smoothly. A sample calculation is applied to a blended wing-body missile type configuration with a top mounted inlet. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 82N25193
NAS 1.60:2012
NASA-TP-2012
L-15053 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/165806 |
