• français
    • English
    français
  • Login
Help
View Item 
  •   Home
  • Dynamique des Fluides (DynFluid)
  • View Item
  • Home
  • Dynamique des Fluides (DynFluid)
  • View Item
JavaScript is disabled for your browser. Some features of this site may not work without it.

Transonic buffet instability: From two-dimensional airfoils to three-dimensional swept wings

Article dans une revue avec comité de lecture
Author
PALADINI, Edoardo
531194 DAAA, ONERA, Université Paris Saclay (COmUE) [Meudon]
BENEDDINE, Samir
531194 DAAA, ONERA, Université Paris Saclay (COmUE) [Meudon]
DANDOIS, Julien
531194 DAAA, ONERA, Université Paris Saclay (COmUE) [Meudon]
SIPP, Denis
531194 DAAA, ONERA, Université Paris Saclay (COmUE) [Meudon]
ccROBINET, Jean-Christophe
492366 Airbus Safran Launchers
134975 Laboratoire de Dynamique des Fluides [DynFluid]

URI
http://hdl.handle.net/10985/17897
DOI
10.1103/physrevfluids.4.103906
Date
2019
Journal
Physical Review Fluids

Abstract

The objective of the present study is to explain the evolution of the transonic buffet phenomenon from two-dimensional airfoils to three-dimensional swept wings by a global stability analysis. With respect to two-dimensional buffet, shock oscillation frequency increases by a factor of 4 to 7 in the case of a swept 30◦ wing and three-dimensional patterns in the detached boundary layer are convected outboard. Crouch et al. [J. Comput. Phys. 224, 924 (2007)] explained the two-dimensional transonic buffet phenomenon by the appearance of a real positive complex eigenvalue of the linearized Jacobian matrix. In the case of an infinite unswept wing, the present study shows that two unstable modes actually exist: The two-dimensional transonic buffet mode already identified by Crouch et al. [J. Fluid Mech. 628, 357 (2009)] and a strongly amplified three-dimensional zerofrequency mode. The latter exhibits regular patterns in the separated boundary layer, which relates to the so-called buffet cells as named by Iovnovich et al. [AIAA J. 53, 449 (2015)]. The nonzero sweep angle generates a spanwise velocity component on the wing which convects the cells outboard. This impacts both modes identified in the unswept case: The two-dimensional mode is weakly damped by the sweep while the three-dimensional buffet cells mode, even if weakly damped, remains strongly unstable and now exhibits a nonzero frequency which increases with the sweep angle. The frequency and wavelength of the most unstable three-dimensional mode for a sweep angle of 30◦ agree well with numerical and experimental values of the three-dimensional transonic buffet on wings. The analysis of the wavemaker of the three-dimensional modes indicates that the core of the instability is nearly solely located in the separated region, with a maximum along the separation line. In contrast, the wavemaker of the two-dimensional buffet mode exhibits stronger values all along the shock wave.

Files in this item

Name:
DYNFLUID_PRF_2019_ROBINET.pdf
Size:
1.971Mb
Format:
PDF
Description:
Article
Embargoed until:
2020-04-21
View/Open

Collections

  • Dynamique des Fluides (DynFluid)

Related items

Showing items related by title, author, creator and subject.

  • Various approaches to determine active regions in an unstable global mode: application to transonic buffet 
    Article dans une revue avec comité de lecture
    PALADINI, Edoardo; MARQUET, Olivier; SIPP, Denis; DANDOIS, Julien; ccROBINET, Jean-Christophe (Cambridge University Press (CUP), 2019)
    The transonic flow field around a supercritical airfoil is investigated. The objective of the present paper is to enhance the understanding of the physical mechanics behind two-dimensional transonic buffet. The paper is ...
  • Analysis and Comparison of Transonic Buffet Phenomenon over Several Three-Dimensional Wings 
    Article dans une revue avec comité de lecture
    PALADINI, Edoardo; DANDOIS, Julien; SIPP, Denis; ccROBINET, Jean-Christophe (American Institute of Aeronautics and Astronautics, 2019)
    The transonic buffet is a complex aerodynamic instability that appears on wings and airfoils at a high subsonic Mach number and/or angle of attack. It consists of a shock oscillation that induces pressure and notably lift ...
  • On the linear receptivity of trailing vortices 
    Article dans une revue avec comité de lecture
    BÖLLE, Tobias; BRION, Vincent; SIPP, Denis; JACQUIN, Laurent; ccROBINET, Jean-Christophe (Cambridge University Press (CUP), 2020)
    The present work investigates the excitation process by which free-stream disturbances are transformed into vortex-core perturbations. This problem of receptivity is modelled in terms of the resolvent in frequency space ...
  • Impinging shear layer instability in over-expanded nozzle dynamics 
    Article dans une revue avec comité de lecture
    TARSIA MORISCO, Cosimo; ccROBINET, Jean-Christophe; HERPE, Julien; SAUCEREAU, Didier (AIP Publishing, 2023-11)
    When rocket engine nozzles operate at a high degree of over-expansion, an internal flow separation occurs with a strong unsteady shock–wave boundary layer interaction. The global dynamics results in a low-frequency mode, ...
  • Global Stability Analyses Unraveling Roughness-induced Transition Mechanisms 
    Article dans une revue avec comité de lecture
    CHERUBINI, Stefania; LERICHE, Emmanuel; ccROBINET, Jean-Christophe; ccLOISEAU, Jean-Christophe (Elsevier, 2015)
    The linear global instability and resulting transition to turbulence induced by a cylindrical roughness element of heighth and diameter d=3h immersed within an incompressible boundary layer flow along a flat plate is ...

Browse

All SAMCommunities & CollectionsAuthorsIssue DateCenter / InstitutionThis CollectionAuthorsIssue DateCenter / Institution

Newsletter

Latest newsletterPrevious newsletters

Statistics

Most Popular ItemsStatistics by CountryMost Popular Authors

ÉCOLE NATIONALE SUPERIEURE D'ARTS ET METIERS

  • Contact
  • Mentions légales

ÉCOLE NATIONALE SUPERIEURE D'ARTS ET METIERS

  • Contact
  • Mentions légales