Journal of Applied Mechanical Engineering

Abstract

Optimum Slat and Flap Configuration for Maximizing Lift on NACA-4412 Airfoil at Various Angle of Attack, Using XFOIL at a Reynolds Number of 1 Million

Parmananda Sharma*, Piyush Kumar and Raj Kumar Singh

In this research paper, we have investigated the optimal configuration of slats and flaps for maximizing lift on the NACA-4412 airfoil at different angles of attack, at a Reynolds number of 1 million. We used XFOIL and python for the simulations and obtained lift, drag, and lift-to-drag ratio for different slat and flap configurations. The slat and flap configuration used was standard, and both the slat and flap angles were varied in the range of 5-15 degrees, resulting in a total of 121 configurations. Additionally, the angle of attack was varied in the range of -5 to 20 degrees with an interval of 0.5 degrees.
Through our study, we have identified the best slat and flap configuration for achieving maximum lift or maximum lift-to-drag ratio for the NACA-4412 airfoil. To validate our results, we used XFLR5 to compare the data generated from XFOIL.
This type of study and simulation is highly relevant for designing flaps and slats, as the lift and drag requirements vary during takeoff and landing of aircraft. By determining the optimal slat and flap configuration, we can improve the performance of aircraft and make them safer and more efficient.

Published Date: 2023-05-29; Received Date: 2023-03-30