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

Authors

232

  1. RS
    Ralf Stark

    Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR), Germany

    12 publications · 338 citations

    11

    h-index

  2. GH
    G. Hagemann

    Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR), Germany

    8 publications · 467 citations

    8

    h-index

  3. MF
    Manuel Frey

    Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR), Germany

    6 publications · 416 citations

    6

    h-index

  4. DP
    Dimitri Papamoschou

    University of California, Irvine, United States

    5 publications · 327 citations

    5

    h-index

  5. MO
    Marcello Onofri

    Sapienza University of Rome, Italy

    4 publications · 143 citations

    4

    h-index

1–5 of 232

Venues

  1. Journal of Propulsion and Power

    10 publications · 321 citations

    10

    h-index

  2. AIAA Journal

    8 publications · 431 citations

    8

    h-index

  3. Shock Waves

    7 publications · 342 citations

    7

    h-index

  4. 37th Joint Propulsion Conference and Exhibit

    Conference · 5 publications · 112 citations

    5

    h-index

  5. NASA Technical Reports Server (NASA)

    Repository · 4 publications · 133 citations

    4

    h-index

1–5