Effect of piezoelectricity in NACA 2421 unsymmetrical aerofoil by using load cell arrangement

Abstract

In this work, the NACA 2421 Aerofoil has been fabricated according to the size of wind tunnel. The effect of piezoelectricity is investigated in the low-speed wind tunnel. The piezoelectric strip is fixed in the 1/4th of the chord point. Due to the effect of piezoelectricity, the flow has ionised and it has suppressed the boundary layer. Due to the suppression, the flow has been maintained as a laminar up to 2/4th of the chord. Due to the laminar flow, the lift is increased and the drag is reduced. It tends to increase the performance of the aircraft. The lift and drag forces are measured directly by using the load cell arrangement. Then, it has been converted into the coefficient of lift and the coefficient of drag and compared with the standard values.

Keywords:

• Three-component balance
• BNC connector
• forces
• moments
• piezoelectric effect
• wind tunnel

Disclosure statement

No potential conflict of interest was reported by the authors.