Flap Effect on Trailing Edge of an Airfoil Simulation by Ansys Fluent

Comprehension of Steady Airflow over a Flapped Airfoil

Project Overview

Using ANSYS Fluent software, this CFD study thoroughly analyzes the constant airflow over a flapping airfoil with an attack angle of 12 degrees.  Detailed CFD studies help us to know the aerodynamic qualities and flow dynamics.

Geometry and Meshing

Model Design

Focusing on capturing the fundamental characteristics of the flapping airfoil, the current model is two-dimensionally constructed using the Design Modeler tool.

Meshing Details

Executed with ANSYS Meshing software, the meshing procedure produced a model of 64,731 elements, so striking a compromise between accuracy and computational efficiency.

Flap Methodology

High-Lift Device Analysis

Reducing the stalling speed of an aircraft wing depends on a flap, which is a high-lift device. Usually installed on the trailing edges of a fixed-wing aircraft, flaps are evaluated for their influence on both lift and drag.

Simulation Parameters

The SST k-omega model is used in this work to properly capture flow patterns and compute drag and lift forces; 45 m/s of velocity interacts with the airfoil.

Results and Conclusion

Flow Contours and Aerodynamic Forces

The solution method reveals two-dimensional contours of turbulent viscosity, pressure, and velocity.  These contours show the pressure disparity between the pressure and suction sides of the airfoil, which is essential for lift creation.  At the leading edge, the stagnation point is also seen; in velocity contours, the wake zone is rather noticeable.

Lift and Drag Coefficients

Moreover, the drag coefficient of the airfoil in the presence of a flap is equal to -0.0273, which is less than airfoil without a flap, where the drag coefficient is equal to -0.0822, which proves that flap presence is effective in drag force reduction that is favorable in aerodynamics applications.