This study aims to evaluate the performance of the Entropic Lattice Boltzmann Method (ELBM) in predicting the aerodynamic forces on a NACA0012 airfoil at high angles of attack. To validate the ac- curacy of the ELBM results, we compare the lift coefficient obtained from simulations with wind tunnel experiments conducted by Sandia National Laboratories [1]. As the angle of attack increases, the lift coefficient of the airfoil becomes nonlinear. At high angles of attack, the lift coefficient experiences a sudden drop, known as the stall. Our focus is on simulating the turbulent flow near the stall region of the airfoil using the higher-order ELBM solver developed in-house by SankhyaSutra Labs (SSL). We choose two angles of attack, 8.2 and 13.2 degrees, to simulate the linear and nonlinear regions of the lift coefficient, respectively. The simulation was performed on the Rudra HPC facility by SankhyaSutra Labs. By investigating the flow characteristics in the near stall region, we aim to provide insights into the stall behavior of the NACA0012 airfoil and improve the accuracy of aerodynamic modeling using ELBM.