CEAS Aeronautical Journal

, Volume 9, Issue 2, pp 339–346 | Cite as

High-speed PIV applied to wake of NASA CRM model at high Re-number sub- and transonic stall conditions

  • Robert KonrathEmail author
  • Reinhard Geisler
  • Janos Agocs
  • Hauke Ehlers
  • Florian Philipp
  • Jürgen Quest
Original Paper


Within the framework of the EU project ESWIRP, the particle image velocimetry (PIV) using high-speed camera and laser has been used to measure the turbulent flow in the wake of a stalled aircraft wing. The measurements took place on the common research model provided by NASA in the pressurized cryogenic European Transonic Wind tunnel. A specific cryoPIV system has been used and adapted for using high-speed PIV components under the cryogenic conditions of the wind tunnel facility. First results are presented comprising transonic and subsonic stall conditions at realistic flight Reynolds numbers of 11.6 and 30 million, respectively.


PIV ETW Common research model High Reynolds number Wing stall Wing wake 



The wind tunnel test campaign has been funded by the European Commission in the 7th framework program. The authors would like to acknowledge the EC for funding this research project and the NASA for their readiness to provide the CRM wind tunnel model. The authors also would like to thank the ESWIRP coordinators and all partners involved in the wind tunnel campaign.


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Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2017

Authors and Affiliations

  1. 1.German Aerospace Center (DLR)Institute of Aerodynamics and Flow TechnologyGöttingenGermany
  2. 2.European Transonic Windtunnel GmbH (ETW)CologneGermany

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