Abstract
The investigation of poststall behavior of a wing was conducted under externally imposed sound. It was observed that acoustic excitation of boundary layer under appropriate frequencies had the potential to provide the extra energy required to modify the severe adverse pressure gradient at or near the stall. The acoustic excitation on a NACA 0012 wing showed suppression of leading-edge separation and improvement in the lift and drag coefficients.
Original language | English |
---|---|
Pages (from-to) | 961-963 |
Number of pages | 3 |
Journal | Journal of Aircraft |
Volume | 38 |
Issue number | 5 |
DOIs | |
Publication status | Published - 2001 |
Externally published | Yes |
ASJC Scopus subject areas
- Aerospace Engineering