Boundary-layer transition detection and structure identification through surface shear-stress measurements Conference Paper uri icon


  • 1997, American Institute of Aeronautics and Astronautics, Inc. Several surface shear-stress measurements are made using hot-film sheet anemometry technology in a three-dimensional, swept-wing boundary layer. Various measurements in the crossflow and streamwise directions are made in regions on the wing surface upstream, through, and downstream of the transition region from laminar to turbulent flow. Advanced analysis techniques including proper orthogonal decomposition (POD), spectra, and spatial correlations are used to identify the presence of flow structure and spatial evolutions within the measured surface shear-stress fields. The resulting spatial eigenmodes from the POD solution across the transition front presents a completely objective method for identifying the start and finish of the transition process in the swept-wing boundary layer. The crossflow POD solutions reveal certain transitional processes and spatial relationships important in understanding flow transition and in developing future flow control algorithms.

published proceedings

  • 36th AIAA Aerospace Sciences Meeting and Exhibit

author list (cited authors)

  • Chapman, K. L., Reibert, M. S., Saric, W. S., & Glauser, M. N.

complete list of authors

  • Chapman, KL||Reibert, MS||Saric, WS||Glauser, MN

publication date

  • January 1998