Abstract
Experiments were conducted at a subsonic Mach number in the Cryogenic Ludwieg-Tube Göttingen to study the influence of surface imperfections on boundary layer transition. Forward-facing steps of different height were installed on two spanwise invariant wind tunnel models and their effect on transition was examined at high chord Reynolds numbers and various streamwise pressure gradients. Transition, detected non-intrusively by means of the Temperature-Sensitive Paint technique, was found to gradually move upstream towards the step location with increasing step Reynolds numbers and relative step height. Larger flow acceleration had a favorable influence on the transition Reynolds number even in the presence of forward-facing steps, but also increased the sensitivity of boundary layer transition to the surface excrescences. The plots of the relative change in transition location as a function of step Reynolds number and relative step height gave good correlations of the results obtained with both wind tunnel models. The correlations were practically independent of the streamwise pressure gradient. Criteria for allowable tolerances on low-sweep Natural Laminar Flow surfaces can now be established from the functional relations determined in this work.
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References
Schrauf, G.: Status and perspectives of laminar flow. Aeronaut. J. 109(1102), 639–644 (2005)
Holmes, B.J., Obara, C.J., Yip, L.P.: Natural laminar flow experiments on modern airplane surfaces. NASA TP 2256 (1984)
Holmes, B.J., Obara, C.J., Martin, G.L., Domack, C.S.: Manufacturing tolerances for natural laminar flow airframe surfaces. SAE Paper No. 850863 (1985)
Nayfeh, A.H.: Influence of two-dimensional imperfections on laminar flow. SAE Paper No. 921990 (1992)
Rizzetta, D.P., Visbal, M.R.: The effect of two-dimensional geometric disturbances on boundary-layer stability. AIAA Paper No. 2013-3108 (2013)
Nenni, J.P., Gluyas, G.L.: Aerodynamic design and analysis of an LFC surface. Aeronaut. Astronaut. 4(7), 52–57 (1966)
Perraud, J.: Laminar-turbulent transition on aerodynamic surfaces with imperfections. In: RTO-AVT-111 (2004)
Wang, Y.X., Gaster, M.: Effect of surface steps on boundary layer transition. Exp Fluids 39, 679–686 (2005)
Crouch, J.D., Kosorygin, V.S., Ng, L.L.: Modeling the effects of steps on boundary layer transition. In: 6th IUTAM Symposium on Laminar-Turbulent Transition, Bangalore, India (2006)
Gerashchenko, S., McKeon, B.J., Westphal, R.V., Bender, A.M., Drake, A.: Hot-wire measurements of the influence of surface steps on transition in favorable pressure gradient boundary layers. AIAA Paper No. 2010–0374 (2010). See also Papers No. 2010–0373 and 2010–0375
Edelmann, C.A., Rist, U.: Impact of forward-facing steps on laminar-turbulent transition in transonic flows without pressure gradient. AIAA J 53(9), 2504–2511 (2015)
Duncan Jr., G.T., Crawford, B.K., Tufts, M.W., Saric, W.S., Reed, H.L.: Effects of step excrescences on a swept wing in a low-disturbance wind tunnel. AIAA Paper No. 2014-0910 (2014)
Kruse, M., Wunderlich, T.F., Heinrich, L.: A conceptual study of a transonic NLF transport aircraft with forward swept wings. AIAA Paper No. 2012-3208 (2012)
Costantini, M., Hein, S., Henne, U., Klein, C., Koch, S., Sachs, W.E., Schojda, L., Rosemann, H., Koop, L., Ondrus, V.: The effect of pressure gradient and a non-adiabatic surface on boundary layer transition investigated by means of TSP. AIAA Paper No. 2013-1137 (2013)
Rosemann, H.: The cryogenic ludwieg-tube tunnel at Göttingen. in: AGARD-R-812; Cologne, Germany, pp. 8-1–8-13 (1996)
Koch, S.: Zeitliche und räumliche Turbulenzentwicklung in einem Rohrwindkanal und deren Einfluss auf die Transition an Profilmodellen. DLR-FB-04-19 (2004)
Fey, U., Egami, Y., Engler, R.: High Reynolds number transition detection by means of temperature-sensitive paint. AIAA Paper No. 2006-0514 (2006)
Costantini, M., Fey, U., Henne, U., Klein, C.: Nonadiabatic surface effects on transition measurements using temperature-sensitive paints. AIAA J 53(5), 1172–1187 (2015)
Tropea, C., Yarin, A.L., Foss, J.F. (eds.): Springer Handbook of Experimental Fluid Mechanics. Springer, Heidelberg (2007). Chap. 7.4: Transition-Detection by Temperature-Sensitive Paint
Northrop Corporation: Final Report on LFC Aircraft Design Data Laminar Flow Control Demonstration Program, NOR-67-136 (1967)
Meyer, F., Kleiser, L.: Numerical Investigation of Transition in 3D Boundary Layers. AGARD-CP-438, Cesme, Turkey, pp. 16-1–16-17 (1988)
Schlichting, H., Gersten, K.: Boundary-Layer Theory. Springer, Berlin, Heidelberg (2000)
Arnal, D.: Boundary layer transition: prediction, application to drag reduction. AGARD Report No. 786, pp. 5-1–5-59 (1992)
Schrauf, G.: LILO, 2.1 - Users Guide and Tutorial. GSSC Technical report 6 (2006)
Dryden, H.L.: Review of published data on the effect of roughness on transition from laminar to turbulent flow. J. Aeronaut. Sci. 20(7), 477–482 (1953)
Tani, I.: Effect of two-dimensional and isolated roughness on laminar flow. In: Lachmann, G.V. (ed.) Boundary Layer and Flow Control, vol. 2, pp. 637–656. Pergamon Press, New York (1961)
Schrauf, G.: COCO—A Program to Compute Velocity and Temperature Profiles for Local and Nonlocal Stability Analysis of Compressible, Conical Boundary Layers with Suction. ZARM Technik report (1998)
Hein, S.: Priv. comm., Institute of Aerodynamics and Flow Technology, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Göttingen, Stefan.Hein@dlr.de (2013)
Acknowledgments
The authors would like to thank: S. Hein (DLR) for the assistance during the definition of the tests and the analysis of the results and for the modification of COCO; C. Fuchs, T. Kleindienst, K. Borchert, and B. Eilerts (DLR) for the constant support during the preparation of the models; S. Koch (DLR) for the assistance during the experimental campaign and the evaluation of the results; U. Henne and W. E. Sachs (DLR) for the help in the TSP data analysis; W. H. Beck (DLR) for the productive conversations; L. Schojda and U. G. Becker (DLR) for the support during the design phase of the PaLASTra model; V. Ondrus (University of Hohenheim) for the chemical development of the Temperature-Sensitive Paint; S. Schaber, A. Wiedemann, D. Meissner (Airbus), R. Kahle, M. Aschoff, and S. Hucke (DNW-KRG) for the support during the test campaign; L. Koop and H. Rosemann (DLR) for the constant advice in this project; U. Fey (DLR) and Y. Egami (Aichi Institute of Technology) for the contribution to the TSP development at DLR in the last decade; W. Schröder (RWTH Aachen), A. Dillmann (DLR), and G. Schrauf (Airbus) for their invaluable advice.
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Costantini, M., Risius, S., Klein, C., Kühn, W. (2016). Effect of Forward-Facing Steps on Boundary Layer Transition at a Subsonic Mach Number. In: Dillmann, A., Heller, G., Krämer, E., Wagner, C., Breitsamter, C. (eds) New Results in Numerical and Experimental Fluid Mechanics X. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 132. Springer, Cham. https://doi.org/10.1007/978-3-319-27279-5_18
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