<p>Hypersonic flow over two generic missile configurations was investigated using CFD meth-</p>
<p>ods. CFD results were compared with experimental results obtained by the hypersonic flight</p>
<p>lab at Texas A&M University. Baseline RANS computations involving the missile configurations at a zero deg angle-of-attack were performed, along with computations at higher angles-of-attack. As the angle-of-attack was increased, complex vortex interactions were observed in the region between the fins. Increasing the angle-of-attack generally increased heating on the windward side of the missile geometries, especially on wall surface regions</p>
<p>adjacent to the fin-root vortices. The results presented highlight observed fin region vortices and regions of intense heating on the body surface. DES simulations methods were also used to explore unsteady aspects of flow around the two generic missile configurations through time-accurate CFD simulations. Power spectral plots were generated to quantify the dominant frequencies of large-scale unsteadiness.</p>
| Identifer | oai:union.ndltd.org:purdue.edu/oai:figshare.com:article/23739768 |
| Date | 25 July 2023 |
| Creators | Matthew Christophe Dean (16642239) |
| Source Sets | Purdue University |
| Detected Language | English |
| Type | Text, Thesis |
| Rights | CC BY 4.0 |
| Relation | https://figshare.com/articles/thesis/Shock-Wave_Boundary-Layer_Interaction_in_Flow_Over_the_High-Speed_Army_Reference_Vehicle/23739768 |
Page generated in 0.0021 seconds