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CEAS Aeronautical Journal

, Volume 9, Issue 2, pp 347–359 | Cite as

Development of flow structures in the near-field wake region of the Common Research Model

  • D.-M. ZimmermannEmail author
  • A. Waldmann
  • T. Lutz
  • E. Krämer
Original Paper

Abstract

The flow in the near-field wake region of a generic transport aircraft configuration has been studied using both unsteady RANS and delayed detached-eddy simulations. The NASA Common Research Model has been used for this purpose, as experimental data obtained with this model in the cryogenic European Transonic Wind Tunnel during the ESWIRP test campaign were available for comparison and validation. Focusing on high angles of attack of \(\alpha = 16^\circ\) and \(\alpha = 18^\circ\), the results form the basis for the study of flow phenomena occurring at stall conditions. Such flight conditions are characterized by massive flow separation at the wing and highly unsteady flow in the wake. In a first step, the numerical results are compared with available test data using global force coefficients and pressure distributions on the wing. Both show a good agreement of numerical and experimental results, indicating slight deviations of the pressure variable at the inboard wing sections. In a second step, the turbulent structures of the near-field wake are examined using the proper orthogonal decomposition method based on snapshots (two-dimensional instantaneous flow fields). Frequencies of the first mode-pair match the dominant frequencies of the lift and velocity wake spectra very well.

Keywords

Common Research Model CFD ESWI\(^{\text {RP}}\) URANS DDES 

Notes

Acknowledgements

The ESWI\(^{\text {RP}}\) project and the measurements were funded by the European Commission in the 7th framework program. We are grateful to NASA (M. Rivers, R. Wahls, and their team) for providing the Common Research Model for the test campaign in the European Transonic Wind Tunnel. Besides that, the research was partly funded within LuFo IV ProWinGS (ATLAS). The authors gratefully acknowledge the support and the computational resources which were provided by the High Computing Center Stuttgart. The simulations were performed on a CRAY XE 40 which is funded by Federal Ministry of Education and Research and the Ministry of Higher Education, Research and Arts Baden-Württemberg.

Conflict of interest

The authors declare that they have no conflict of interest.

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Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2016

Authors and Affiliations

  1. 1.Institute of Aerodynamics and Gas DynamicsUniversity of StuttgartStuttgartGermany

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