| タイトル | Experimental and theoretical aerodynamic characteristics of a high-lift semispan wing model |
| 本文（外部サイト） | http://hdl.handle.net/2060/19900010730 |
| 著者（英） | Applin, Zachary T.; Gentry, Garl L., Jr. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1990-05-01 |
| 言語 | eng |
| 内容記述 | Experimental and theoretical aerodynamic characteristics were compared for a high-lift, semispan wing configuration that incorporated a slightly modified version of the NASA Advanced Laminar Flow Control airfoil section. The experimental investigation was conducted in the Langley 14- by 22-Foot Subsonic Tunnel at chord Reynolds numbers of 2.36 and 3.33 million. A two-dimensional airfoil code and a three-dimensional panel code were used to obtain aerodynamic predictions. Two-dimensional data were corrected for three-dimensional effects. Comparisons between predicted and measured values were made for the cruise configuration and for various high-lift configurations. Both codes predicted lift and pitching moment coefficients that agreed well with experiment for the cruise configuration. These parameters were overpredicted for all high-lift configurations. Drag coefficient was underpredicted for all cases. Corrected two-dimensional pressure distributions typically agreed well with experiment, while the panel code overpredicted the leading-edge suction peak on the wing. One important feature missing from both of these codes was a capability for separated flow analysis. The major cause of disparity between the measured data and predictions presented herein was attributed to separated flow conditions. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 90N20046
NASA-TP-2990
NAS 1.60:2990
L-16441 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/138619 |
