Summary
Measurements of the temporal and spatial development of natural and controlled boundary layer instabilities in the linear and weakly nonlinear stage of transition were carded out using a laminar wing glove in-flight and in a wind tunnel. An 74 piezo-sensor-array and a spanwise hot-wire array together with several independent point sources for the controlled experiments were used. Depending on the excitation case, typical structures which characterize fundamental and the oblique breakdown were observed. The results of natural transition show two-dimensional Tollmien- Schlichting waves in the linear stage as well as three-dimensional wave packets in the beginning of nonlinear stage, and were observed during flight and in the wind tunnel. Comparing in-flight and wind tunnel measurements, the disturbance structures are qualitatively similar, but the amplification of 3D instabilities occurs later and more rapidly in the wind tunnel.
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Peltzer, I., Nitsche, W. (2006). In-Flight and Wind Tunnel Investigalions of Instabilities on a Laminar Wing Glove. In: Rath, HJ., Holze, C., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics V. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 92. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-33287-9_28
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DOI: https://doi.org/10.1007/978-3-540-33287-9_28
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