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WP-1 Reference Cases of Laminar and Turbulent Interactions

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Transition Location Effect on Shock Wave Boundary Layer Interaction

Part of the book series: Notes on Numerical Fluid Mechanics and Multidisciplinary Design ((NNFM,volume 144))

Abstract

In order to be able to judge the effectiveness of transition induction in WP-2, reference flow cases were planned in WP-1. There are two obvious reference cases—a fully laminar interaction and a fully turbulent interaction. Here it should be explained that the terms “laminar” and “turbulent” interaction refer to the boundary layer state at the beginning of interaction only. There are two basic configurations of shock wave boundary layer interaction and these are a part of the TFAST project. One is the normal shock wave, which typically appears at the transonic wing and on the turbine cascade. The characteristic incipient separation Mach number range is about M = 1.2 in the case of a laminar boundary layer and about M = 1.32 in the case of turbulent boundary layer. The second typical flow case is the oblique shock wave reflection. The most characteristic case in European research is connected to the 6th FP IP HISAC project concerning a supersonic business jet. The design speed of this airplane is M = 1.6. Therefore the TFAST consortium decided to use this Mach number as the basic case. Pressure disturbance at this Mach number is not very high and can be compared to the disturbance of the normal shock at the incipient separation Mach number mentioned earlier. As mentioned earlier, shock reflection at M = 1.6 may be related to incipient separation. Therefore two additional test cases were planned with different Mach numbers. ITAM conducted an M = 1.5 test case, and TUD an M = 1.7 test case. These partners have also previously made very specialized and successful contributions to the UFAST project.

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Authors and Affiliations

  1. Aix-Marseille University, CNRS, IUSTI, Marseille, France

    Jean-Paul Dussauge, Pierre Dupont, Sébastien Piponniau & Lionel Larchevêque

  2. Office National d’Etudes et de Recherches Aérospatiales, Meudon, France

    Reynald Bur

  3. University of Cambridge, Cambridge, UK

    Todd Davidson & Holger Babinsky

  4. University of Rome, La Sapienza, Rome, Italy

    Matteo Bernardini & Sergio Pirozzoli

  5. Delft University of Technology, Aerodyn. Lab., Delft, The Netherlands

    Rogier Giepman, Ferry Schrijer & Bas van Oudheusden

  6. Russian Academy of Sciences, Siberian Branch, Inst.of Theor. App. Mech., Novosibirsk, Russia

    Pavel Polivanov & Andrey Sidorenko

  7. Institut de Mécanique des Fluides de Toulouse, UMR 5502 CNRS-INPT-UT3, Toulouse, France

    Damien Szubert, Marianna Braza, Ioannis Asproulias, Nikos Simiriotis, Jean-Baptiste Tô & Yannick Hoarau

  8. University of Southampton, Southampton, UK

    Andrea Sansica & Neil Sandham

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  1. Jean-Paul Dussauge
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Correspondence to Jean-Paul Dussauge .

Editor information

Editors and Affiliations

  1. Institute of Fluid Flow Machinery, Polish Academy of Sciences, IMP PAN, Gdansk, Poland

    Piotr Doerffer

  2. Institute of Fluid Flow Machinery, Polish Academy of Sciences, IMP PAN, Gdansk, Poland

    Pawel Flaszynski

  3. Supersonic Group, IUSTI, Marseille, France

    Jean-Paul Dussauge

  4. Department of Engineering, University of Cambridge, Cambridge, UK

    Holger Babinsky

  5. Rolls-Royce Deutschland Ltd, Blankenfelde-Mahlow, Germany

    Patrick Grothe

  6. German Aerospace Center (DLR), Institute of Propulsion Technology, Göttingen, Niedersachsen, Germany

    Anna Petersen

  7. Aircraft Engineering and Loads Division, Dassault Aviation, Saint-Cloud, France

    Flavien Billard

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Dussauge, JP. et al. (2021). WP-1 Reference Cases of Laminar and Turbulent Interactions. In: Doerffer, P., et al. Transition Location Effect on Shock Wave Boundary Layer Interaction. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 144. Springer, Cham. https://doi.org/10.1007/978-3-030-47461-4_2

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  • DOI: https://doi.org/10.1007/978-3-030-47461-4_2

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  • Online ISBN: 978-3-030-47461-4

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