Flow visualization of swept wing boundary layer transition

Flow visualization of swept wing boundary layer transition

Serpieri, J.
Kotsonis, M.

Aerospace Engineering

Aerospace Structures & Computational Mechanics

2015-06-15

In this work the flow visualization of the transition pattern occurring on a swept wing in a subsonic flow is presented. This is done by means of fluorescent oil flow technique and boundary layer hot-wire scans. The experiment was performed at Reynolds number of 2:15 . 106 and at angle of attack of -3º. At these conditions, three different flows are investigated: a natural transition case and two other ones where instead the transition mechanism, the stationary cross-flow waves, was forced with discrete roughness elements. Previously published results on similar flows were confirmed for two of the three tested configurations (natural transition and boundary layer forcing at the wavelength of the dominant stationary mode) while, for the third one (where a sub-critical wavelength was forced), some discrepancies are observed. A parametric study on the effect of the Reynolds number and the angle of attack is also presented.

3D subsonic boundary layer transition
cross-flow stationary waves
oil flow visualization
hot-wire

http://resolver.tudelft.nl/uuid:383c1163-245d-47a7-bd0c-1f2229fb1849

Universita di Napoli Federico II

978-88-906484-3-4

Proceedings of the 10th Pacific Symposium on Flow Visualization and Image Processing, Naples, Italy, 15-18 June 2015

Institutional Repository

conference paper

(c) 2015 The Author(s)