Airfoil trailing-edge noise up to a Reynolds number based on chord of 2.96 x 10 to the 6th power was studied. Comparisons are made with current theory, particularly with regard to the nature of the pressure field in the vicinity of the trailing-edge and its influence on the radiated noise.
An experimental investigation of trailing-edge noise
1979-06-01
Report
No indication
English
AIAA | 1976
|