| タイトル | Incompressible boundary-layer stability analysis of LFC experimental data for sub-critical Mach numbers |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860017742 |
| 著者（英） | Berry, S. A. |
| 著者所属（英） | Joint Inst. for Advancement of Flight Sciences |
| 発行日 | 1986-07-01 |
| 言語 | eng |
| 内容記述 | An incompressible boundary-layer stability analysis of Laminar Flow Control (LFC) experimental data was completed and the results are presented. This analysis was undertaken for three reasons: to study laminar boundary-layer stability on a modern swept LFC airfoil; to calculate incompressible design limits of linear stability theory as applied to a modern airfoil at high subsonic speeds; and to verify the use of linear stability theory as a design tool. The experimental data were taken from the slotted LFC experiment recently completed in the NASA Langley 8-Foot Transonic Pressure Tunnel. Linear stability theory was applied and the results were compared with transition data to arrive at correlated n-factors. Results of the analysis showed that for the configuration and cases studied, Tollmien-Schlichting (TS) amplification was the dominating disturbance influencing transition. For these cases, incompressible linear stability theory correlated with an n-factor for TS waves of approximately 10 at transition. The n-factor method correlated rather consistently to this value despite a number of non-ideal conditions which indicates the method is useful as a design tool for advanced laminar flow airfoils. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 86N27214
NASA-CR-3999
NAS 1.26:3999 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/153929 |
