| タイトル | Variable Sweep Transition Flight Experiment (VSTFE)-Parametric Pressure Distribution Boundary Layer Stability Study and Wing Glove Design Task |
| 本文（外部サイト） | http://hdl.handle.net/2060/19880019510 |
| 著者（英） | Rozendaal, Rodger A. |
| 著者所属（英） | Boeing Commercial Airplane Co. |
| 発行日 | 1986-06-01 |
| 言語 | eng |
| 内容記述 | The Variable Sweep Transition Flight Experiment (VSTFE) was initiated to establish a boundary-layer transition data base for laminar flow wing design. For this experiment, full-span upper-surface gloves will be fitted to a variable sweep F-14 aircraft. The results of two initial tasks are documented: a parametric pressure distribution/boundary-layer stability study and the design of an upper-surface glove for Mach 0.8. The first task was conducted to provide a data base from which wing-glove pressure distributions could be selected for glove designs. Boundary-layer stability analyses were conducted on a set of pressure distributions for various wing sweep angles, Mach numbers, and Reynolds number in the range of those anticipated for the flight-test program. The design procedure for the Mach 0.8 glove is described, and boundary-layer stability calculations and pressure distributions are presented both at design and off-design conditions. Also included is the analysis of the clean-up glove (smoothed basic wing) that will be flight-tested initially and the analysis of a Mach 0.7 glove designed at the NASA Langley Research Center. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 88N28894
NASA-CR-3992
NAS 1.26:3992
D6-52511 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
