CFD Simulation of Flow over NACA 0012 Airfoil

EasyChair Preprint no. 7972

Abstract

Fluid flow over a NACA airfoil (NACA 0012) was simulated using ANSYS FLUENT. A two-dimensional steady state simulation was conducted along with SST k- ω turbulence model. Grid independency was established and study was done by varying Reynolds number and angle of attack over a range of 5x105 to 2x106 and -15o to 15o, respectively. Lift and drag coefficients were calculated from the simulations and compared with their experimental values. An excellent agreement was noted for the coefficient of lift. However, some discrepancies were observed and highlighted for the coefficient of drag. Specifically, the simulated values of drag coefficients were 30 to 100% higher than the experimental values. The discrepancies are attributed to the selection of turbulence model and 2-D steady state flow. Over the range of parametric variation in this study, both lift and drag coefficients increased with an increase in the angle of attack. The effect of variation in Reynolds number was minor. The coefficient of drag decreased with Reynolds number, whereas the coefficient of lift remained almost unchanged.

Keyphrases: Airfoil, CFD, NACA 0012

@Booklet{EasyChair:7972,
  author = {Tejasvi Singh and Gaurav Mittal and Sanchit Mittal and Riya Tyagi},
  title = {CFD Simulation of Flow over NACA 0012 Airfoil},
  howpublished = {EasyChair Preprint no. 7972},

  year = {EasyChair, 2022}}