| Popis: |
The effects of flow control devices for an axisymmetric external compression supersonic inlet are investigated. Specifically, vortex generators (VGs) are placed in the subsonic diffuser to decrease radial distortion at the diffuser exit. The performance of these devices is evaluated for both a single-stream inlet and a dual-stream inlet, incorporating engine bypass. Without the VGs, both inlets yielded thick boundary layers on the hub-side at the exit of the diffuser. The single-stream inlet was found to have a very low external wave strength while the dual-stream inlet showed less shock-induced centerbody boundary layer separation. In both cases, the addition of vortex generators was found to be effective at decreasing boundary layer axisymmetric shape factor, with vane vortex generators resulting in the largest improvement. |
