| LDR | | 02926nam u200457 4500 |
| 001 | | 000000418326 |
| 005 | | 20190215162755 |
| 008 | | 181129s2018 |||||||||||||||||c||eng d |
| 020 | |
▼a 9780438016804 |
| 035 | |
▼a (MiAaPQ)AAI10745569 |
| 035 | |
▼a (MiAaPQ)purdue:22332 |
| 040 | |
▼a MiAaPQ
▼c MiAaPQ
▼d 247004 |
| 082 | 0 |
▼a 629.1 |
| 100 | 1 |
▼a Chynoweth, Brandon C. |
| 245 | 10 |
▼a Measurements of Transition Dominated by the Second-Mode Instability at Mach 6. |
| 260 | |
▼a [S.l.]:
▼b Purdue University.,
▼c 2018. |
| 260 | 1 |
▼a Ann Arbor:
▼b ProQuest Dissertations & Theses,
▼c 2018. |
| 300 | |
▼a 267 p. |
| 500 | |
▼a Source: Dissertation Abstracts International, Volume: 79-10(E), Section: B. |
| 500 | |
▼a Adviser: Steven P. Schneider. |
| 502 | 1 |
▼a Thesis (Ph.D.)--Purdue University, 2018. |
| 520 | |
▼a Hypersonic boundary-layer transition can be caused by many different mechanisms. This research focuses on studying the growth and breakdown of the second-mode instability. Experiments were performed in the Boeing/AFOSR Mach-6 Quiet Tunnel locate |
| 520 | |
▼a Using a flared cone model, measurements were first made with a smooth wall to characterize natural second-mode transition. As the second-mode amplitude increased up to a maximum of nearly 30% of the mean static pressure, streamwise streaks of he |
| 520 | |
▼a Under noisy flow conditions, Marineau has shown that a linear correlation exists between the edge Mach number and the maximum second-mode amplitude prior to breakdown. He has used this relationship to develop a more physics-based transition pred |
| 520 | |
▼a The effect of well controlled roughness elements interacting with the second-mode instability was investigated using the Rod Insertion Method (RIM) roughness inserts. Three different aspects of the roughness elements were studied. For RIM insert |
| 520 | |
▼a Experimental data for the flared cone at a stagnation pressure of 140 psia was compared to direct numerical simulations performed by Christoph Hader at the University of Arizona. The data compared well qualitatively showing many of the same tren |
| 520 | |
▼a Experiments were performed under quiet flow conditions on a 2.5° and 3° half-angle straight cones to measure second-mode transition without the effect of surface curvature. The goal of these slender cones was to measure the maximum second-mode m |
| 590 | |
▼a School code: 0183. |
| 650 | 4 |
▼a Aerospace engineering. |
| 650 | 4 |
▼a Engineering. |
| 690 | |
▼a 0538 |
| 690 | |
▼a 0537 |
| 710 | 20 |
▼a Purdue University.
▼b Aeronautics and Astronautics. |
| 773 | 0 |
▼t Dissertation Abstracts International
▼g 79-10B(E). |
| 773 | |
▼t Dissertation Abstract International |
| 790 | |
▼a 0183 |
| 791 | |
▼a Ph.D. |
| 792 | |
▼a 2018 |
| 793 | |
▼a English |
| 856 | 40 |
▼u http://www.riss.kr/pdu/ddodLink.do?id=T14996861
▼n KERIS
▼z 이 자료의 원문은 한국교육학술정보원에서 제공합니다. |
| 980 | |
▼a 201812
▼f 2019 |
| 990 | |
▼a ***1012033 |