| タイトル | Fluidic scale model multi-plane thrust vector control test results |
| 著者（英） | Shieh, Chih F.; Wing, David J.; Chiarelli, Charles; Johnsen, Raymond K. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1993-06-01 |
| 言語 | eng |
| 内容記述 | An experimental investigation has been conducted at the NASA Langley 16-Foot Transonic Tunnel Static Test Facility to determine the concept feasibility of using fluidics to achieve multiplane thrust vector control in a 2D convergent-divergent (2D-CD) fixed aperture nozzle. Pitch thrust vector control is achieved by injection of flow through a slot in the divergent flap into the primary nozzle flow stream. Yaw vector control results from secondary air delivered tangentially to vertical Coanda flaps. These flaps are offset laterally and aligned parallel to the primary nozzle side walls. All tests were conducted at static (no external flow) conditions. Flow visualization was conducted using a paint flow technique and Focus Schlieren. Significant levels of pitch deflection angles (19 deg) were achieved at low pressure ratios and practical levels (14 deg) resulted at typical intermediate power settings. The ability of the Coanda surface blowing concept to produce yaw deflection was limited to NPR not greater than 4. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 93A50187
AIAA PAPER 93-2433 |
| 権利 | Copyright |
