Point-source induced transition in free flight
Chapter
Summary
This paper reports on experimental and numerical results, which were obtained during the course of work of the joint university research group “Natürliche Transition”. Main target of the investigations was the downstream development of an artificially induced point source disturbance in a decelerated transitional boundary layer in free flight. Experimental results obtained through in-flight measurements and numerical results from Direct Numerical Simulations of the twodimensional adverse pressure gradient flow over a wing glove on a motorglider are presented and compared qualitatively and quantitatively.
Keywords
Wall Shear Stress Direct Numerical Simulation Pressure Fluctuation Wave Train Direct Numerical Simulation Data
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.
Preview
Unable to display preview. Download preview PDF.
References
- [1]Suttan, J., Baumann, M., Fühling, S., Erb, P., Becker, S. and Stemmer, C., In-Flight Research on Boundary Layer Transition — Works of the DFG-University Research Group. In: H. Körner and R. Hilbig (eds.), Notes on Numerical Fluid Mechanics, vol. 60, pp. 343-350. Vieweg Verlag (1997), 10th Stab Symposium 96, Braunschweig.Google Scholar
- [2]Rist, U. and Fasel, H., Direct numerical simulation of controlled transition in a flat-plate boundary layer. J. Fluid Mech., 298, 211–248 (1995).CrossRefMATHGoogle Scholar
- [3]Kloker, M., Direkte Numerische Simulation des laminar-turbulenten Strömungsumschlages in einer stark verzögerten Grenzschicht Dissertation, Universität Stuttgart (1993).Google Scholar
- [4]Jeong, J. and Hussain, F., On the identification of a Vortex. J. Fluid Mech., 285, 69–94 (1995).MathSciNetCrossRefMATHGoogle Scholar
- [5]Sturzebecher, D. and Nitsche, W., Visualization of the Spatial-Temporal Instability Wave Development in a Laminar Bouindary Layer by Means of a Heated PVDF Sensor Array. In: H. Körner and R. Hilbig (eds.), Notes on Numerical Fluid Mechanics, vol. 60, pp. 335-342. Vieweg Verlag (1997), 10th Stab Symposium 96, Braunschweig.Google Scholar
- [6]Nitsche, W., Bose, S., Haselbach, F. and Suttan, J., Capabilities of Surface Measurement Techniques and their Impact on Modern Wing-Design and Assessment. ICAS-98-3.3.4 (1998), 21st Congress of the International Council of the Aeronautical Sciences, Melbourne, Australia.Google Scholar
- [7]Erb, P., Ewald, B. and Roth, M., Flight experiment guidance technique for research on transition with Grob G109 aircraft of the Technische Hochschule Darmstadt. In: H. Körner and R. Hilbig (eds.), Notes on Numerical Fluid Mechanics, vol. 60, pp. 143-150. Vieweg Verlag (1997), 10th Stab Symposium 96, Braunschweig.Google Scholar
- [8]Stemmer, C., Kloker, M. and Wagner, S., DNS of Harmonic Point Source Disturbances in an Airfoil Boundary Layer. AIAA Paper 98-2436 (1998), 29th AIAA Fluid Dynamics Conference, Albuquerque, NM.Google Scholar
Copyright information
© Springer Fachmedien Wiesbaden 1999