Flow Unstart Phenomena
Flow Unstart Phenomena is a transient aerodynamic instability in supersonic combustion systems, characterized by the abrupt detachment of the terminal shock wave from the inlet, leading to a breakdown of stable supersonic flow and resulting in a sudden loss of engine performance.
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4.9K
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253
Authors
80
Institutions
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2017–2026
25
Variants
Inlet Unstart
Parents
104
Experimental Investigation of Unstart in an Inlet/Isolator Model in Mach 5 Flow
Justin L. Wagner, Kemal Yuceil, Agustin Valdivia et al. · AIAA Journal · 2009 · 334 citations
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Nanjing University of Aeronautics and Astronautics
Nanjing, China
11 h-index
38 publications
2.1K citations
The University of Texas at Austin
Austin, United States
8 h-index
34 publications
3K citations

Harbin Institute of Technology
Harbin, China
7 h-index
28 publications
2K citations

United States Air Force Research Laboratory
Wright-Patterson AFB, United States
5 h-index
6 publications
113 citations

National University of Defense Technology
Changsha, China
4 h-index
18 publications
502 citations

Glenn Research Center
Cleveland, United States
4 h-index
6 publications
170 citations
Stanford University
Stanford, United States
4 h-index
11 publications
877 citations
University of Science and Technology of China
Hefei, China
4 h-index
12 publications
664 citations
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16 publications · 908 citations
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12 publications · 982 citations
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AST · 7 publications · 191 citations
7
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5 publications · 134 citations
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3 publications · 112 citations
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