Abstract
An experimental study involving interaction of concentrated streamwise wing tip vortices and normal shock fronts was carried out in a Mach 2.49 flow. The interaction scheme involved positioning a vortex-generator wing section upstream of a pitot type normal shock inlet such that the wing tip vortices interacted with the normal shock formed in front of the inlet. The vortex strength was varied by placing the vortex generator wing at different angles of attack while a normal shock was created by adjusting the mass flow rate passing through the inlet. Spark shadowgraphs, laser sheet planar visualizations, and pitot pressure measurements of the flowfield indicated a significant change in the structure of streamwise vortices generated by the vortex generator wing at 5 and 10 degrees angle of attack upon encountering a normal shock discontinuity. Results of the investigation showed that the interactions lead to the formation of an unsteady conical shock wave far upstream of the inlet as well as a highly turbulent flow downstream for both vortices. Pitot pressure measurements using a fast response pressure transducer in conjunction with the spark shadowgraphs revealed a bimodal feature of the flowfield. The frequency of oscillation of the generated structure was found to be higher for increased vortex strength.
| Original language | English (US) |
|---|---|
| Title of host publication | Fluid Dynamics Conference |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Pages | 1-13 |
| Number of pages | 13 |
| State | Published - 1995 |
| Event | Fluid Dynamics Conference, 1995 - San Diego, United States Duration: Jun 19 1995 → Jun 22 1995 |
Other
| Other | Fluid Dynamics Conference, 1995 |
|---|---|
| Country/Territory | United States |
| City | San Diego |
| Period | 6/19/95 → 6/22/95 |
ASJC Scopus subject areas
- Aerospace Engineering
- Mechanical Engineering
- Fluid Flow and Transfer Processes
- Energy Engineering and Power Technology