Abstract
Modification of the flow separation characteristics of a laminar airfoil using a remotely located high-power laser was experimentally investigated in a low-speed, low-turbulence wind tunnel. A laminar airfoil model (chord length of 500 mm) was designed and fabricated to emulate the flight characteristics of a small aircraft. At 0 deg angle of attack, the airfoil model was determined to have an incipient laminar separation bubble on its lifting surface between 67 and 80% chord. A strong laser-induced breakdown was generated 2 mm upstream of the leading edge by focusing a collimated beam emitted from a 900 mW laser at 1064 nm through a convex lens. The high-temperature plasma generates a shock wave and a cell of heated air that travels along the airfoil lifting surface and interacts with the boundary-layer flow. Two-component particle image velocimetry was used to map the transient and steady-state flow. The hot, low-density fluid induced significant exchange of momentum between the freestream and the incipient separation zone, leading to reattached flow for a period lasting seven orders of magnitude longer than the plasma lifetime. These results show promise that laser-based energy-deposition approaches can be used for effective flow-control applications.
Recommended Citation
A. Bright et al., "Boundary-Layer Separation Control using Laser-Induced Air Breakdown," AIAA Journal, vol. 56, no. 4, pp. 1472 - 1482, American Institute of Aeronautics and Astronautics, Jan 2018.
The definitive version is available at https://doi.org/10.2514/1.J055272
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Full Access
International Standard Serial Number (ISSN)
0001-1452
Document Type
Article - Journal
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 2018
