Experiments involving a three-element airfoil (30P30N) fitted with various slat cove- and flap cove-filler configurations were carried out in order to characterize the aerodynamic and aeroacoustic behavior of the cove-fillers. The tests were completed for a wide range of angles of attack and Reynolds numbers (4.6 × 105 to 1.1 × 106). Aerodynamic measurements included, lift and drag measurements, mean and unsteady surface pressure measurements, mean velocity profiles, Reynolds stress profiles and flow visualization around the slat and flap region for all the aforementioned configurations. Lift and drag measurement showed insignificant difference amongst the tested cove filler configurations compared to the baseline. Mean surface pressure measurement results show that the aerodynamic performances were not significantly affected by the application of slat cove-filler for the tested flow condition. The mean velocity contour results from the Particle Image Velocimetry measurements show a highly energized vortex present within the slat cove region of the baseline case and it was eliminated by the application of slat cove-filler. Vortices found within in the flap cove region were completely eliminated by the application of flap cove-filler. Proper Orthogonal Decomposition analysis for all the configurations detailing on the coherent structures formed within the slat cove shear layer and slat wake was also presented. The wall-pressure spectra acquired using the flush mounted transducers shows narrowband and broadband components for the baseline case. The application of slat cove-fillers completely eliminated the narrowband spectra generated by the vortices inside the slat cove. However, the slat cove-filler appears to increase the overall broadband at the low and mid-frequency range in the airfoil near-field.
|Title of host publication
|2018 24th AIAA/CEAS Aeroacoustics Conference
|American Institute of Aeronautics and Astronautics Inc. (AIAA)
|Number of pages
|Published - 25 Jun 2018