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<title>Feasibility study to build a smart rotor: trailing edge flap actuation</title>

1993; SPIE; Volume: 1917; Linguagem: Inglês

10.1117/12.152762

1996-756X

Dhananjay K. Samak, Inderjit Chopra,

Wind and Air Flow Studies

This paper presents an experimental study on the development of a Froude scale helicopter rotor blade with trailing edge flap as a vibration reduction device actuated by piezoelectric crystals. A fixed wing model with NACA 0012 airfoil, 3.0 inch blade chord and 20% trailing edge flap is fabricated and tested in the open-jet tunnel to determine the dynamic flap response at various blade angles of attack and excitation frequencies. The results show that for a given velocity, flap response does not change appreciably with the excitation frequency and the blade angle of attack.