Title: Flow separation control in a two-airfoil system by trailing edge modification and active flow control

Authors: Deepak Kumar Singh; Dilip Lalchand Parmar; Arjun Sharma

Addresses: Department of Applied Mechanics, Indian Institute of Technology Delhi, New Delhi – 110016, India ' Department of Applied Mechanics, Indian Institute of Technology Delhi, New Delhi – 110016, India ' Department of Applied Mechanics, Indian Institute of Technology Delhi, New Delhi – 110016, India

Abstract: Numerical simulations of flow past a NACA0012 airfoil with a slotted flap are conducted using steady Reynolds-averaged Navier Stokes equations at Reynolds number of 5 × 10⁴ and 5° angle of attack in freestream. The ratio of chord lengths of flap to main airfoil is 0.2. The lower side of main airfoil surface is modified to incorporate a cusped trailing edge. The effects of a cusped trailing edge on flow over flap region are studied at different values of flap deflection angles, in the range 12°-25°. A cusped trailing edge has a significant effect on boundary layer evolution on flap surface. The presence of cusp reduces viscous effects in slot flow, increases flow speed at the trailing edge and aligns the flow along flap suction surface. Maximum enhancement in lift coefficient of about 13% is achieved by using active flow control along with a cusped trailing edge for the main element.

Keywords: high-lift system; boundary layer separation; active flow control.

DOI: 10.1504/PCFD.2023.134897

Progress in Computational Fluid Dynamics, An International Journal, 2023 Vol.23 No.6, pp.352 - 363

Received: 25 Jul 2022
Accepted: 10 Oct 2022
Published online: 16 Nov 2023 *

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