Learning Goals

In this module, you'll learn to:

• Develop the solution to a 2D turbulent airfoil flow problem in ANSYS Fluent
• Describe how the governing equations need to be modified to account for turbulence
• Validate the numerical results from ANSYS Fluent by comparing with experimental data provided by NASA

Problem Specification

This module is drawn from MAE 5230 Intermediate Fluid Dynamics at Cornell University.

Flow past airfoils is a well-studied canonical problem which is very useful for learning how to apply CFD software to practical problems and for gaining physical insights about flow past streamlined bodies. Here, we consider the flow past the classic NACA 0012  airfoil at an angle of attack of 10 degrees.

The input parameters we'll use are:

• Airfoil chord length = 1 m
• Free-stream velocity = 51.45 m/s
• Density = 1.1767kg/m^3
• Coefficient of viscosity =1.009 \\times 10^{-5} \\frac{kg}{m s}

The corresponding Reynolds number is 6 million. We'll determine the velocity and pressure fields around the airfoil by solving the relevant governing equations using ANSYS Fluent. We'll validate the results by comparing the following parameters with experimental data provided by NASA.

• Pressure coefficient variation over the airfoil
• Lift and drag coefficients

참고사이트

Turbulence Modeling Resource