In this paper a passive method for airfoil tonal noise reduction using segmented elastic panel airfoil configuration is proposed. Numerical investigation using perturbation evolution method is carried out at a low chord based Reynolds number of 5 × 104, Mach number of 0.4 and an angle of attack of 5◦. The approach of employing a resonant elastic panel on the airfoil surface has shown promising tonal noise reduction potential up to 2.1 dB. The idea is extended in the present study by employing multiple segmented elastic panels on the airfoil surface based on the localized flow characteristics over the airfoil surface. Five different panel configurations are designed and their effectiveness in terms of tonal noise reduction is evaluated and compared with baseline configuration. The acoustic and structural analyses show that the airfoil configuration mounted with two elastic panels located at the onset of sharp growth of boundary layer instabilities can significantly enhance the noise reduction potential by 52% as compared to the single panel airfoil configuration. The mutual inter-dynamical relationship among the panels strongly influence the panel vibrational behavior and their effectiveness in noise reduction.