Inviscid Flow Around The Wing, CFD Simulation ANSYS Fluent Training

$121.00 Student Discount

In this project, Inviscid Fluid Flow Over the wing  has been simulated and the results of this simulation have been investigated.

This product includes Geometry & Mesh file and a comprehensive Training Movie.
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Description

Inviscid fluid flow Introduction

A wing is a type of fin that produces lift while moving through air or other fluid. Accordingly, wings have streamlined cross-sections subject to aerodynamic forces and act as airfoils. A wing’s aerodynamic efficiency is expressed as its lift-to-drag ratio.

The design and analysis of aircraft wings are one of the principal applications of the science of aerodynamics, which is a branch of fluid mechanics. In principle, the airflow properties around any moving object can be found by solving the Navier-Stokes equations of fluid dynamics. However, these equations are notoriously difficult to solve except for simple geometries, and simpler equations are used. For a wing to produce lift, it must be oriented at a suitable angle of attack. When this occurs, the wing deflects the airflow downwards as it passes the wing. Since the wing exerts a force on the air to change its direction, it must also exert an equal and opposite force on the wing.

Inviscid fluid flow Description

In this project, we simulate a wing with ANSYS Fluent software. In addition to this, this project aims to stimulate the inviscid flow around the wing and obtain the pressure and velocity around it.

Geometry and mesh

The geometry of the solution consisted of Geometric defining parameters, including chord line, angle of attack, leading-edge, and trailing edge. The 3D geometry of this project has been produced with ANSYS Design Modeler software:

Mesh is created with ANSYS Meshing software, and the mesh type is unstructured. The number of cells is 5558992.

We consider several assumptions to simulate the present model:

  • We perform a pressure-based solver.
  • The simulation is steady.
  • The gravity effect on the fluid is ignored.

The following table represents a summary of the defining steps of the problem and its solution:

 

 

Models

 

 

viscous

 

inviscid
 

Boundary conditions

 

 

airfoil

 

 

 

 

wall

 

 

 

 

inlet

 

 

 

 

Velocity inlet

 

 

velocity

 

30 m/s

 

 

outlet

 

 

 

 

 

 

 

Pressure outlet

 

gauge pressure

 

0 Pascal

 

Sym1

 

 

symmetry

 

Sym2

 

 

Symmetry

 

Solution Methods

 

 

Pressure-velocity coupling

 

 

Coupled

 

 

Spatial discretization

 

 

pressure

 

second-order

 

momentum

 

second-order upwind

 

 

Initialization

 

 

Initialization method

 

 

Standard

 

Run calculation

 

 

 

 

 

Number of time step

 

120

Results

In this simulation, three-dimensional contours are related to pressure, velocity, etc., are presented. Pressure and velocity results The results section shows that, as expected, the maximum velocity was found at the top level of the airfoil, while the maximum pressure was at the front edge, where the speed was at the minimum and occurred at the stagnation point. A stagnation point in the flow, where the velocity of a fluid is zero. Stagnation points exist at the surface of objects in the flow field, where the flow is brought to rest by the thing.

You can obtain Geometry & Mesh file and a comprehensive Training Movie that presents how to solve the problem and extract all desired results.

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