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Nozzle Flow Separation

Published:1998-09 Issue:9 Volume:36 Page:1618-1625
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Romine G. L.¹

Affiliation:

1. Lockheed Martin Astronautics, Denver, Colorado 80201

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/2.588

Reference12 articles.

1. SHOCK-INDUCED BOUNDARY LAYER SEPARATION IN OVER-EXPANDED CONICAL EXHAUST NOZZLES

2. Schilling,M. “Flow Separation in a Rocket Nozzle,” M.S. Thesis, Graduate School of Arts and Sciences,Univ. of Buffalo, Buffalo,NY, June 1962.

3. Prandtl, L., Essentials of Fluid Dynamics, Blackie, Glasgow, Scotland, UK, pp.266, 269, 276 (translation).

Cited by 29 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Numerical Study of Wall Heat Transfer Effects on Flow Separation in a Supersonic Overexpanded Nozzle;Energies;2023-02-10

2. On the unsteady dynamics of partially shrouded compressible jets;Experiments in Fluids;2021-10

3. On the fluidic behavior of an over-expanded planar plug nozzle under lateral confinement;Physics of Fluids;2020-08-01

4. Transient conjugate heat transfer in critical flow nozzles;International Journal of Heat and Mass Transfer;2017-01

5. Shock-Induced Boundary-Layer Separation in Round Convergent–Divergent Nozzles;AIAA Journal;2016-02

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