Title: Streamlining fluid flow: injection slot optimisation for co-flow jet airfoil

Authors: Vigneswaran Chidambaram Mahalakshmi; Inamul Hasan; Srinath Ramakrishnan; Somashekar Venkateshappa

Addresses: Department of Aerospace Engineering, Ramaiah Institute of Technology, Bangalore, Karnataka, India ' Department of Aerospace Engineering, Ramaiah Institute of Technology, Bangalore, Karnataka, India ' Department of Aerospace Engineering, Dayananda Sagar University, Bangalore, Karnataka, India ' Department of Aeronautical Engineering, Nitte Meenakshi institute of technology, Bangalore, Karnataka, India

Abstract: This research explores the strategic optimisation of injection slot placement on a NACA 0018 co-flow jet (CFJ) airfoil, with the objective of enhancing aerodynamic efficiency while mitigating energy consumption. The precise location of the injection slot is pivotal, as it governs the effectiveness of boundary layer control, augmenting lift and delaying separation, while simultaneously influencing the power demands of the CFJ system's pump. A comprehensive computational analysis is conducted using a pressure-based solver, resolving the Reynolds-averaged Navier-Stokes (RANS) equations for two-dimensional, incompressible flow. The simulations are performed under sea-level boundary conditions, with a Mach number of 0.1 and a Reynolds number of 0.65 million, utilising the Spalart-Allmaras turbulence model. The results demonstrate that optimal injection slot placement enhances the lift coefficient by up to 30.1% while concurrently reducing power consumption. This research articulates a refined aerodynamic optimisation framework for CFJ systems, advancing both lift and energy efficiency for broader aviation applications.

Keywords: aerodynamics; flow control; boundary layer; lift; drag; co-flow jet; CFJ airfoil.

DOI: 10.1504/PCFD.2025.147799

Progress in Computational Fluid Dynamics, An International Journal, 2025 Vol.25 No.4, pp.201 - 212

Received: 12 Sep 2024
Accepted: 25 Oct 2024
Published online: 01 Aug 2025 *

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