| LDR | | 00000nam u2200205 4500 |
| 001 | | 000000436018 |
| 005 | | 20200228112215 |
| 008 | | 200131s2019 ||||||||||||||||| ||eng d |
| 020 | |
▼a 9781392839904 |
| 035 | |
▼a (MiAaPQ)AAI27712099 |
| 035 | |
▼a (MiAaPQ)OhioLINKosu1560352886647369 |
| 040 | |
▼a MiAaPQ
▼c MiAaPQ
▼d 247004 |
| 082 | 0 |
▼a 629.1 |
| 100 | 1 |
▼a Stack, Cory M. |
| 245 | 10 |
▼a Turbulence Mechanisms in a Supersonic Rectangular Multistream Jet with an Aft-Deck. |
| 260 | |
▼a [S.l.]:
▼b The Ohio State University.,
▼c 2019. |
| 260 | 1 |
▼a Ann Arbor:
▼b ProQuest Dissertations & Theses,
▼c 2019. |
| 300 | |
▼a 232 p. |
| 500 | |
▼a Source: Dissertations Abstracts International, Volume: 81-05, Section: B. |
| 500 | |
▼a Advisor: Gaitonde, Datta. |
| 502 | 1 |
▼a Thesis (Ph.D.)--The Ohio State University, 2019. |
| 506 | |
▼a This item must not be sold to any third party vendors. |
| 520 | |
▼a Over the last 80 years, high-performance military aircraft have relied on increasingly sophisticated jet engine technologies to enable performance and fulfill mission requirements. To satisfy these engineering demands, several reliable technologies are often combined into one composite engine configuration. Although the behavior of these composite configurations is fairly well known at the engineering level, their rapid advancement is constrained by a lack of knowledge of the fundamental fluid dynamics, particularly the dominant unsteady turbulent mechanisms. This has in turn limited the effectiveness of design tools. Nozzle designs are also becoming more exotic as they conform to increasingly complicated emerging engine architectures, such as variable-cycle engines, whose flowfields are inherently complex due to the multitude of compressible shear layers that evolve in the presence of pressure gradients. The flowfield complexity is further exacerbated for supersonic flight where the engine is integrated into the airframe, and the turbulent, high-speed, shock-containing exhaust interacts with proximal surfaces of the aircraft.In this work, high-fidelity Large-Eddy Simulations are employed to examine the fluid dynamics of a nozzle configuration relevant to emerging airframe-integrated variable-cycle engine architectures. The nozzle comprises two rectangular streams |
| 590 | |
▼a School code: 0168. |
| 650 | 4 |
▼a Aerospace engineering. |
| 690 | |
▼a 0538 |
| 710 | 20 |
▼a The Ohio State University.
▼b Aero/Astro Engineering. |
| 773 | 0 |
▼t Dissertations Abstracts International
▼g 81-05B. |
| 773 | |
▼t Dissertation Abstract International |
| 790 | |
▼a 0168 |
| 791 | |
▼a Ph.D. |
| 792 | |
▼a 2019 |
| 793 | |
▼a English |
| 856 | 40 |
▼u http://www.riss.kr/pdu/ddodLink.do?id=T15494739
▼n KERIS
▼z 이 자료의 원문은 한국교육학술정보원에서 제공합니다. |
| 980 | |
▼a 202002
▼f 2020 |
| 990 | |
▼a ***1816162 |
| 991 | |
▼a E-BOOK |