Abstract
An experimental and numerical investigation has been performed to study the evolution of shock waves undergoing a sudden expansion in one direction while restricted in the second. Experimental data are gathered and studied for shock waves undergoing the sudden 4:l area expansion in air for Mach numbers of 1.5 and 2.0. Detailed, time-accurate measurements of the shock wave and vortex core location as well as wall pressure data are presented. In addition, the evolving flow structure through the time-accurate flowfield imagery is also presented. The results of these experiments are compared to twodimensional numerical simulations specific to the Mach 1.5 and 2.0 initial conditions and geometry. The direct comparisons of the experimental work and numerical simulations provide insight into flowfield phenomena such as viscous dissipation and shock/vortex interaction. The data presented in this effort further elucidates key modeling questions by providing time-accurate flow visualization and pressure data of a two-dimensional shock wave undergoing a sudden expansion in a confined chamber.
| Original language | English |
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| Publication status | Published - 2000 |
| Externally published | Yes |
| Event | 38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States Duration: 10 Jan 2000 → 13 Jan 2000 |
Conference
| Conference | 38th Aerospace Sciences Meeting and Exhibit 2000 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 10/01/00 → 13/01/00 |