Nozzle Flow Separation
Nozzle Flow Separation is a fluid dynamic phenomenon in rocket propulsion systems wherein the boundary layer of the exhaust flow detaches from the nozzle wall due to adverse pressure gradients, leading to asymmetric flow and degraded thrust vector control performance.
111
Publications
3.8K
Citations
232
Authors
82
Institutions
Publications per year
2017–2026
17
Parents
111
Numerical investigation of separated nozzle flows
C. L. Chen, S. R. Chakravarthy, C. M. Hung · AIAA Journal · 1994 · 121 citations
1–5 of 111
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Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR), Germany
12 publications · 338 citations
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Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR), Germany
8 publications · 467 citations
8
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Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR), Germany
6 publications · 416 citations
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4
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1–5 of 232
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Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR)
Cologne, Germany
10 h-index
18 publications
748 citations
Office National d'Études et de Recherches Aérospatiales
Palaiseau, France
6 h-index
16 publications
608 citations
University of California, Irvine
Irvine, United States
5 h-index
8 publications
442 citations

Langley Research Center
Hampton, United States
5 h-index
10 publications
512 citations

Nanjing University of Aeronautics and Astronautics
Nanjing, China
5 h-index
12 publications
288 citations
National Aerospace Laboratories
Bengaluru, India
4 h-index
5 publications
149 citations

Sapienza University of Rome
Rome, Italy
4 h-index
10 publications
362 citations
Boeing (Australia)
Brisbane, Australia
3 h-index
4 publications
52 citations
1–8 of 82
10 publications · 321 citations
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8 publications · 431 citations
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7 publications · 342 citations
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Conference · 5 publications · 112 citations
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Repository · 4 publications · 133 citations
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