Flow separation from the leading edge of an airfoil and the effect of acoustic perturbations on the separated flow
Abstract
The structure of the separated flow at the leading edge of a symmetrical airfoil is investigated by thermoanemometry in a low-turbulence subsonic wind tunnel. It is shown that the superposition of an acoustic field leads to a reattachment of the boundary layer and an elimination of global flow separation. The hysteresis effect of the acoustic field on the reattachment of the separated boundary layer is examined.
- Publication:
-
PMTF Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki
- Pub Date:
- April 1985
- Bibcode:
- 1985PMTF.......112K
- Keywords:
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- Acoustic Excitation;
- Airfoil Profiles;
- Boundary Layer Separation;
- Leading Edges;
- Reattached Flow;
- Subsonic Wind Tunnels;
- Hysteresis;
- Low Turbulence;
- Velocity Measurement;
- Fluid Mechanics and Heat Transfer