Aerodynamic Coefficient of Airfoil for Ultra-Low Reynolds Number
With modern micro-air-vehicle developments, the need for aerodynamics understanding becomes important. The proper design of the airfoil is very helpful in fulfilling the aerodynamic concept. The flow around the airfoil can be considered ultra-low Reynolds number when it is less than 10,000 and carried out by the Navier-Stokes solver for incompressible. This solution can be approached using the Lattice Boltzmann Method (LBM). Flow simulations were carried out at Re=500 and Re=1000 with variations of the angle of attack of 30 each from 0 to 29 degree with an additional angle of 1 degree. Each simulation was carried out on 40 airfoils designed using NURBS and two NACAs. The simulation results with LBM produce the lift and drag coefficients for each airfoil.
Steps to reproduce
1. Install Python 2. Install Python package: numpy (v1.22.2), matplotlib (v3.5.1), pytorch (v1.12.1) and tqdm (v4.62.3) 3. Run the simulation in terminal: python main.py