Performance analysis of NACA2411 ice accreted original and optimized airfoils

In present day, icing on the aircraft body has become the threat to the aircraft flight safety. Thus, it is vital to study the influential effects of ice accretion over airfoil in aerodynamic characteristics. The standard NACA2411 airfoil is chosen for this research study. The NACA 2411 airfoil has been optimized by using Genetic Algorithm method. Ice accretion over original NACA2411 and GA 011timizcd ai1foils is carried out using Eulerian based droplet im11ingement code/method. The com1mtational fluid dynamics (CFD) analysis for original ice accreted and optimized ice accreted airfoils have been done to obtain performance results and therefore lift coefficient and drag coefficient are found in fluent solver. The performance analysis of NACA2411 original ice accreted and optimized ice accreted airfoils are compared. And from the study, the performance of ice accreted original airfoil is estimated to be less efficient than ice accreted optimized airfoil.