Abstract
The transonic flow around the 65° Delta wing configuration with sharp leading edge is presented. The occurrence of shock on delta wings introduces complex shock/vortex interactions, particularly at moderate-to-high angles of incidence. These interactions can make a significant difference to the vortex breakdown. Transonic vortical flow and vortex breakdown is one aspect of the second "International Vortex Flow Experiment" (VFE-2). This investigation considers complex flowfield the 65° Delta wing using modified delayed detached eddy simulation(MDDES) . The time-averaged pressure is compared with the experiment data to validate the method. The shocks in the flow field are investigated and the interaction of the vortex and the shock waves is also studied. The unsteady characteristic of the vortex breakdown is analyzed by studying the Power Spectral Density (PSD) of time history of density at the probe points.
| Original language | English |
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| Pages | 1645-1656 |
| Number of pages | 12 |
| State | Published - 2012 |
| Event | 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 - Brisbane, Australia Duration: 23 Sep 2012 → 28 Sep 2012 |
Conference
| Conference | 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 |
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| Country/Territory | Australia |
| City | Brisbane |
| Period | 23/09/12 → 28/09/12 |
Keywords
- Cross-flow shock
- MDDES
- Shock/vortex interactions
- Vortex breakdown