Project

CFD ANALYSIS OF FLOW OVER AN AIRFOIL

AAnkit Kumawat22 Jun 2020

AIM: TO RUN A FLOW SIMULATION FOR FLOW OVER AN AIRFOIL USING SOLIDWORKS CFD.

OBJECTIVE:

To create a model of a NACA0017 airfoil.
To perform Flow simulation study.
To obtain a plot for velocity variation at a cut plane.
To obtain a plot for pressure variation at a cut plane.
To calculate and plot the lift force.
To calculate and plot the drag force.
To compare the lift and drag forces for following conditions-

Study number	Angle of attack
1	0 degree
2	2 degree
3	4 degree
4	6 degree
5	8 degree
6	10 degree

OVERVIEW:

An airfoil is a device which gets a useful reaction from air moving over its surface. When an airfoil is moved through the air, it is capable of producing lift. Wings, horizontal tail surfaces, vertical tails surfaces, and propellers are all examples of airfoils. Generally, the wing of small aircraft will look like the cross-section of the figure above. The forward part of an airfoil is rounded and is called the leading edge. The aft part is narrow and tapered and is called the trailing edge. A reference line often used in discussing airfoils is the chord, an imaginary straight line joining the extremities of the leading and trailing edges.

Bernoulli's Principle: The pressure of a fluid (liquid or gas) decreases at points where the speed of the fluid increases. In other words, Bernoulli found that within the same fluid, in this case air, high speed flow is associated with low pressure, and low speed flow with high pressure. This principle was first used to explain changes in the pressure of fluid flowing within a pipe whose cross-sectional area varied. In the wide section of the gradually narrowing pipe, the fluid moves at low speed, producing high pressure. As the pipe narrows it must contain the same amount of fluid. In this narrow section, the fluid moves at high speed, producing low pressure.

An important application of this phenomenon is made in giving lift to the wing of an airplane, an airfoil. The airfoil is designed to increase the velocity of the airflow above its surface, thereby decreasing pressure above the airfoil. Simultaneously, the impact of the air on the lower surface of the airfoil increases the pressure below. This combination of pressure decrease above and increase below produces lift. The upward component of this force is lift; the backward component is drag.

PROCEDURE:

Firstly, we will generate the NACA0017 Airfoil and save it as a text file

Now inserting the Airfoil

Providing Angle of attack to the Airfoil

To start the flow simulation, we will provide some initial conditions like Unit System, Fluid type, Analysis type, Thermodynamic parameters etc.

Unit System

Fluid type

Analysis type

Wall conditions

Thermodynamic parameters

Now defining the computational domain for the study

To refine the meshing, we will provide the local mesh

Setting up the Goals(Lift and Drag forces)

Creating Cut plane for Pressure

Creating Cut plane for Velocity

Then by clicking on the “run”

RESULTS:

Study-1 (0-degree Angle of attack)

Velocity

Pressure

Lift force

Drag force