K. Alt, K. Thamm, M. Corelli Grappadelli, R. von Soldenhoff, H. Lüdeke, P. Scholz

A traverseable flow probe was developed to measure boundary layer data for laminar boundary layers over suction skins. Boundary layer data is a key to verify transition predictions and to exactly trace the development of instabilities in laminar boundary layers. Measurement of boundary layer data is particularly intricate over micro-porous surfaces used for laminar flow control, because any probe must me mounted well downstream of the suction area. The probe presented herein can traverse a single-element hot-wire in, both, streamwise and wall-normal direction over distances of 365mm and 52 mm, respectively, with a stiffness and accuracy making it suitable to measure velocity profiles of boundary layers, but also amplitude functions of Tollmien-Schlichting waves. The probe is modular and can be used in two different large-scale experimental setups with flat plates. Some boundary layer profiles, including suction for laminar flow control, will be shown taken from an entry in the wind tunnel MUB.

Deutscher Luft- und Raumfahrtkongress 2023, Stuttgart

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

urn:nbn:de:101:1-2023120412351665421770

10.25967/610146

Laminar Flow Control, Boundary Layer Suction, Laminar Boundary Layer

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Alt, K.; Thamm, K.; et al. (2023): A Traversable Flow Probe to measure Laminar Boundary Layer Properties over Suction Skins. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/610146. urn:nbn:de:101:1-2023112913300908208016.

29.11.2023