Title: Experimental and computational study on a morphed trailing edge airfoil for enhanced lift and stall characteristics

Authors: Krish V. Raibole; Kundlik V. Mali

Addresses: Department of Mechanical Engineering, Dr. Vishwanath Karad MIT World Peace University, Survey No. 124, Paud Rd., Kothrud, Pune, Maharashtra 411038, India; Indian Institute of Technology Bombay, Main Gate Rd., IIT Area, Powai, Mumbai, Maharashtra 400076, India ' Department of Mechanical Engineering, Dr. Vishwanath Karad MIT World Peace University, Survey No. 124, Paud Rd., Kothrud, Pune, Maharashtra 411038, India

Abstract: The current study presents a morphed trailing edge methodology applied to a Clark-Y airfoil in order to improve the effective stall angle of the specific airfoil under definite conditions. A morph of 2° was provided to the trailing edge of the Clark-Y airfoil in consideration. The performance of the morphed wing was analysed by varying two parameters, the angle of attack (AOA) and the freestream flow velocity. The AOA was varied from 0° to 50°, while the flow stream velocity was 10 m/s and 12 m/s. The morphed airfoil showed a maximum increase in the lift-to-drag ratio at 15° and 10 m/s flow velocity. Although at the cost of lift force and a minor increase in drag, the stall angle of the airfoil is improved from 22° to 25°. Numerical simulations showed a maximum deviation of 12.7% with the experimental data, affirming the reliability of the simulations and the methodology.

Keywords: morphed; trailing edge; airfoil; stall; angle of attack; AOA; drag; lift.

DOI: 10.1504/IJSA.2025.145728

International Journal of Sustainable Aviation, 2025 Vol.11 No.1, pp.99 - 114

Received: 15 Jul 2024
Accepted: 11 Dec 2024
Published online: 17 Apr 2025 *

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