# Airflow Around a NACA Airfoil CFD Simulation

~~$116.00~~ $40.00

This project is going to simulate an airfoil in the airflow field with a 16-degree attack angle.

This ANSYS Fluent project includes CFD simulation files and a training movie.

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## Description

## Airfoil Project Description

This project is going to simulate an airfoil in the airflow field. Geometric defining parameters include chord line, angle of attack, leading-edge, and trailing edge. The direction of the airflow into the body is defined by the angle of attack (the angle between the chord and the horizontal direction of the airflow velocity). The purpose of this paper is to investigate the behavior of airflow and pressure distribution, as well as to study drag and lift forces.

In the present case, the angle of attack is 16 degrees and the length of the chord and the width of the airfoil are assumed to be equal to 1. Thus, to determine the drag force, the length of the chord must be multiplied by the sine 16 and then across the cross-section width, and to define the lift force, the chord length must be multiplied by the cosine 16 multiplied by the cross-section and then across the width. Therefore, the surface area for calculating the lift and drag forces is equal to the following values, which are defined in the reference values section.

The following figure gives a schematic of the structure of an asymmetric and its defining geometric parameters:

**(**Airfoil**)**

## Airfoil **Geometry & Mesh**

The 2-D geometry of the present model is drawn using the Design Modeler software. First, the coordinates of the points in the wall forming of the desired airfoil are imported to the software, and then, using the called points, it is completely drawn in the software. The far-field boundary required for the analysis of airflow behavior is then drawn around the airfoil according to the relevant standards. The figure below shows an overview of the model’s geometry.

The meshing of the present model has been done using ANSYS Meshing software. The mesh type is unstructured and the element number is equal to 296533. The figure below shows a view of the meshing.

**(**Airfoil**)**

**Airflow around an Airfoil CFD Simulation**

To simulate the present model, we consider several assumptions, which are:

- The pressure-based solver is performed.
- We do not simulate the heat transfer.
- The present model is steady.
- We do not consider the effect of gravity on the fluid.

The following is a summary of the steps for defining the problem and its solution:

Models (Airfoil) | ||

k-epsilon | Viscous model | |

RNG | k-epsilon model | |

enhanced wall treatment | near-wall treatment | |

Velocity inlet | Inlet | |

20.78736 m.s^{-1} | velocity magnitude | (Airfoil) |

Pressure 0utlet | Outlet | |

0 pascal | gauge pressure | |

wall | Airfolil’s wall | |

stationary wall | wall motion | |

AirfoilSolution Methods () | ||

SIMPLE | Pressure-velocity coupling | |

second order | pressure | Spatial discretization |

second order upwind | momentum | |

second order upwind | turbulent kinetic energy | |

second order upwind | turbulent dissipation rate | |

Initialization | ||

Hybrid | Initialization method |

## Results

At the end of the airfoil solution process, we obtain two-dimensional contours of pressure, velocity, turbulent kinetic energy, as well as two-dimensional pathlines. Also, the value of drag and lift coefficient and forces have been obtained.

Drag force and drag coefficient are equal to:

Lift force and drag coefficient are equal to:

We obtain the drag and lift coefficients for an airfoil with an attack angle of 16 degrees along the length and width of the unit (1):

We compare the values of the lift coefficient with the value in the diagram in the reference:

**(**Airfoil**)**

**(**Airfoil**)**

All files, including Geometry, Mesh, Case & Data, are available in Simulation File. By the way, Training File presents how to solve the problem and extract all desired results.

There are some free products to check the service quality.

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