High-speed PIV applied to wake of NASA CRM model at high Re-number sub- and transonic stall conditions
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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.
KeywordsPIV 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.
- 1.Seifert, A., Pack, L.G.: Oscillatory excitation of unsteady compressible flows over airfoils at flight Reynolds numbers. Proc. of 37th AIAA Aerospace Sciences Meeting and Exhibit, Reno NV, 11–14 Jan, AIAA 99-0925 (1999)Google Scholar
- 2.Molton, P., Bur, R., Lepage, A., Brunet, V., Dandois, J.: Control of buffet phenomenon on a transonic swept wing. Proc. of 40th fluid dynamics conference and exhibit, 28 June–1 July, Chicago, Illinois, AIAA 2010-4595 (2010)Google Scholar
- 3.Quest, J., Leuckert, J., Fey, U., Konrath, R, Egami, Y.: Development and application of modern measurement techniques for pressurized cryogenic wind tunnels. Proc. of 26th International congress of the aeronautical sciences, ICAS 2008, Anchorage (Alaska, USA), 14–19 September, CP-261, pp 1–12 (2008)Google Scholar
- 4.Lutz, Th., Gansel, P.P., Godard, J.-L., Gorbushin, A., Konrath, R., Quest, J., Rivers, S.M.B.: Going for experimental and numerical unsteady wake analyses combined with wall interference assessment by using the NASA CRM model in ETW. Proc. of 51st AIAA aerospace sciences meeting, AIAA Paper 2013-0871 (2013)Google Scholar
- 5.Rivers, M.B., Rudnik, R., Quest, J.: Comparisons of NTF, Ames and ETW results on the CRM. Proc. of 53st AIAA aerospace sciences meeting, Kissimmee (Florida/USA), 5–9 January, AIAA Paper 2015-1093 (2015)Google Scholar
- 6.Konrath, R., Agocs, J., Geisler, R., Otter, D., Roosenboom, E.W.M., Wolf, Th., Quest, J.: Flow field measurements by PIV at high Reynolds numbers. Proc. of 51st AIAA aerospace sciences meeting, Kissimmee (Florida/USA), 5–9 January, AIAA Paper 2013-0869 (2013)Google Scholar
- 7.Konrath, R., Agocs, J., Geisler, R., Otter, D., Roosenboom, E., Quest J.: Wing wake measurements at high Reynolds numbers by means of cryo PIV, Proc. of 10th Intern. Symp. on particle image Velocimetry—PIV13, Delft (NL), July 1-3 (2013)Google Scholar
- 8.Raffel, M., Willert, C.E., Wereley, S.T., Kompenhans, J.: Particle image velocimetry—a practical guide, 2nd edn. Springer, Berlin (2007)Google Scholar
- 9.Lutz, Th., Gansel, P.P., Waldmann, A., Zimmermann, D-M., Schulte am Hülse. S.: Time-resolved prediction and measurement of the wake past the CRM at high Reynolds number stall conditions, Proc. of 53st AIAA aerospace sciences meeting, Kissimmee (Florida/USA), 5–9 January, AIAA Paper 2015-1094 (2015)Google Scholar