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Unsteadiness of Flow Separation and End-Effects Regime in a Thrust-Optimized Contour Rocket Nozzle

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Abstract

Turbulent flow separation in over-expanded rocket nozzles is investigated experimentally in a sub-scale model nozzle fed with cold air and having a thrust-optimized contour. Depending upon the pressure ratio either a free shock separation (FSS) or a restricted shock separation (RSS) is observed with a significant hysteresis between these two flow regimes. It is shown that the RSS configuration may involve several separated regions. Analysis of wall pressure fluctuations give quantitative information on the fluctuating pressure field directly connected with the occurrence of significant side loads. Direct measurements of the evolution of the side loads with respect to the pressure ratio show the occurrence of three distinct peaks which are explained by the wall pressure fluctuations measurements.

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Authors and Affiliations

  1. Laboratoire d'Etudes Aérodynamiques, UMR CNRS/ENSMA 6609, 43 Route de l'Aérodrôme, 86036, Poitiers Cedex, France

    Anh Thi Nguyen, H. Deniau, S. Girard & T. Alziary de Roquefort

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  1. Anh Thi Nguyen
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  2. H. Deniau
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  3. S. Girard
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  4. T. Alziary de Roquefort
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Nguyen, A.T., Deniau, H., Girard, S. et al. Unsteadiness of Flow Separation and End-Effects Regime in a Thrust-Optimized Contour Rocket Nozzle. Flow, Turbulence and Combustion 71, 161–181 (2003). https://doi.org/10.1023/B:APPL.0000014927.61427.ad

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  • DOI: https://doi.org/10.1023/B:APPL.0000014927.61427.ad

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