Abstract
Planar laser sheet visualizations of the flowfield generated by the interaction of a streamwise wing tip vortex and a strong oblique shock front at several distances downstream of a shock generating wedge were performed in a Mach 2.49 flow. The experimental scheme involved positioning a two-dimensional wedge surface downstream of a vortex generator wing section so that the wing-tip vortex interacts with the planar oblique shock front. The results of the investigation revealed an expansion of the vortex core in crossing a strong oblique shock front. The maximum vortex core diameter was seen to occur at a distance of 12.7 mm downstream of the wedge leading edge while at distances further downstream, the vortex core diameter remained approximately constant. The vortical structure was observed to persist along the entire chord of the shock generating wedge but was seen to diffuse with distances downstream of the wedge leading edge. Measurements of the vortex position relative to the wedge surface indicated that immediately downstream of the normal portion of a bulged-forward shock wave, the vortex axis was parallel to the direction of the freestream flow. On the other hand, the vortex was observed to travel parallel to the wedge surface at distances downstream of the wedge mid-chord position. The conical structure which forms as a result of vortex distortion was found to be sensitive to downstream disturbances in a manner similar to the incompressible vortex breakdown.
| Original language | English (US) |
|---|---|
| State | Published - 1996 |
| Event | 34th Aerospace Sciences Meeting and Exhibit, 1996 - Reno, United States Duration: Jan 15 1996 → Jan 18 1996 |
Other
| Other | 34th Aerospace Sciences Meeting and Exhibit, 1996 |
|---|---|
| Country/Territory | United States |
| City | Reno |
| Period | 1/15/96 → 1/18/96 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering