| LDR | | 03127nmm uu200469 4500 |
| 001 | | 000000330669 |
| 005 | | 20240805161921 |
| 008 | | 181129s2017 |||||||||||||||||c||eng d |
| 020 | |
▼a 9780438098190 |
| 035 | |
▼a (MiAaPQ)AAI10901878 |
| 035 | |
▼a (MiAaPQ)OhioLINK:osu1511734224701396 |
| 040 | |
▼a MiAaPQ
▼c MiAaPQ
▼d 248032 |
| 082 | 0 |
▼a 530 |
| 100 | 1 |
▼a Waindim, Mbu. |
| 245 | 10 |
▼a On Unsteadiness in 2-D and 3-D Shock Wave Turbulent Boundary Layer Interactions. |
| 260 | |
▼a [S.l.] :
▼b The Ohio State University.,
▼c 2017 |
| 260 | 1 |
▼a Ann Arbor :
▼b ProQuest Dissertations & Theses,
▼c 2017 |
| 300 | |
▼a 200 p. |
| 500 | |
▼a Source: Dissertation Abstracts International, Volume: 79-12(E), Section: B. |
| 500 | |
▼a Adviser: Datta Gaitonde. |
| 502 | 1 |
▼a Thesis (Ph.D.)--The Ohio State University, 2017. |
| 520 | |
▼a Shock-boundary layer interactions (SBLIs) are ubiquitous occurrences in supersonic and hypersonic vehicles and have the tendency to inhibit their structural and aerodynamic performance. For example, in the inlets and isolators of such vehicles, |
| 520 | |
▼a Nominally 2-D interactions have been studied extensively and have identified low-frequency shock motions which lead to undesirable pressure loads. The particular frequencies associated with the motions have been characterized using time resolved |
| 520 | |
▼a For flow fields where the shock is swept, a complex 3-D interaction is encountered whose unsteady features are even less well understood. The mean structure of these 3-D interactions has been obtained experimentally and using RANS simulations, a |
| 520 | |
▼a Although Large Eddy Simulations (LES) are invaluable for characterizing time evolving features, they are prohibitively expensive for swept interactions. A stability analysis based method, the Mean Flow Perturbation (MFP) technique appears as a b |
| 520 | |
▼a A systematic verification and validation of the technique is presented to provide a solid basis for its employment. By implementing the technique on canonical problems with similar properties as the swept interaction, its applicability for flows |
| 520 | |
▼a By definition, the implementation of MFP requires the knowledge of a mean base state. For the nominally 2-D interactions, the mean of a previously obtained LES is used as the basis. In addition to providing the input to the MFP technique, the LE |
| 520 | |
▼a Besides the LES supplied mean base state, the MFP technique is also implemented with a RANS supplied base flow. No significant differences in the results are observed indicating a relative independence of the MFP technique to the base flow gener |
| 590 | |
▼a School code: 0168. |
| 650 | 4 |
▼a Physics. |
| 650 | 4 |
▼a Aerospace engineering. |
| 690 | |
▼a 0605 |
| 690 | |
▼a 0538 |
| 710 | 20 |
▼a The Ohio State University.
▼b Aero/Astro Engineering. |
| 773 | 0 |
▼t Dissertation Abstracts International
▼g 79-12B(E). |
| 773 | |
▼t Dissertation Abstract International |
| 790 | |
▼a 0168 |
| 791 | |
▼a Ph.D. |
| 792 | |
▼a 2017 |
| 793 | |
▼a English |
| 856 | 40 |
▼u http://www.riss.kr/pdu/ddodLink.do?id=T15000304
▼n KERIS |
| 980 | |
▼a 201812
▼f 2019 |
| 990 | |
▼a 관리자 |