| タイトル | Improving CAP-TSD steady pressure solutions through airfoil slope modification |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960049881 |
| 著者（英） | Batina, John T.; Mitterer, Kent F.; Maughmer, Mark D.; Silva, Walter A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1996-08-01 |
| 言語 | eng |
| 内容記述 | A modification of airfoil section geometry is examined for improvement of the leading edge pressures predicted by the Computational Aeroelasticity Program - Transonic Small Disturbance (CAP-TSD). Results are compared with Eppler solutions to assess improvement. Preliminary results indicate that a fading function modification of section slopes is capable of significant improvements in the pressures near the leading edge computed by CAP-TSD. Application of this modification to airfoil geometry before use in CAP-TSD is shown to reduce the nonphysical pressure peak predicted by the transonic small disturbance solver. A second advantage of the slope modification is the substantial reduction in sensitivity of CAP-TSD steady pressure solutions to the computational mesh. |
| NASA分類 | Aerodynamics |
| レポートNO | 96N34082
NASA-TM-110214
NAS 1.15:110214 |
| 権利 | No Copyright |
