Numerical Study of Improving the Aerodynamic Performance of the High Lift Devices in the Two-Element Airfoil

Document Type : Original Article

Authors

• Meysam Izadi ¹
• Arash shams taleghani ²
• Reza Khaki ³

¹ PhD candidate, Aerospace Research Institute

² Aerospace Research Institute

³ Assoc. Prof. Shahid Sattari Aeronautical University

10.22067/jacsm.2022.79293.1142

Abstract

The aim of this research is to improve the aerodynamic performance of a NACA-23012 airfoil equipped with a High lift device by changing its geometric parameters. In this research, Navier-Stokes equations are solved in turbulent and incompressible flow conditions using Fluent software. After the airfoil and flap modeling process, at different flap angles (5 to 30 degrees), unstructured meshing was produced in Gambit software and the improvement of aerodynamic performance due to changes in geometric parameters was investigated. The flow is assumed to be steady, turbulent and incompressible, and the algorithm for solving the equations is also selected as pressure-based. The flow Reynolds range is 3.6*10⁶ and the turbulence model used is realizable k-epsilon. Comparison of the results and aerodynamic characteristics of the airfoil equipped with a flap after making changes in the geometric parameters in the Fluent software, shows that the aerodynamic coefficients are improved significantly (about 15%) and also the flow separation is shifted towards the end of the flap. Also, the investigation of the pressure and velocity gradients at different stages show that the changes are very effective and better distributed compared to the reference article.

Keywords

• High Lift Devices
• Single Slotted Flaps
• Aerodynamic Optimization
• Unstructured Grid

Main Subjects

• Aerodynamics

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