Flow over an airfoil

Airfoil:

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.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.

PROCEDURE:

1.The geometry was created using the coordinates provided along with the challenge.

2. After creating the geometry, the sketch was closed and extruded to get the design ready.

3.this was set up in flow simulation to achieve our objective.

4. inlet is 5-10 times of chord length

5. outlet is 10-15 times of chord length

6. mesh of the airfoil was refined at the edges and size was appropriately adjusted.

7. Cut plots were introduced.

Velocity=500 ms-1

AOA- 0 degree

DRAG=152.38N

LIFT=1.94N

From the velocity & Pressure cut plot, Air stream of velocity 500 m/s flows over the airfoil, it is split into two equal streams.

AOA-2 degree

DRAG=175.15N

LIFT=638.371N

AOA=4 degrees

DRAG=238.064N

LIFT=1307.17N

AOA=6 deg

DRAG=357.587N

LIFT=2.1KN

AOA=8 deg

DRAG=508.85N

LIFT=2.63KN

AOA=10 degrees

OBSERVATIONS:

As the angle of attack increases the value of lift increases and drag too. But this is possible upto a critical AOA only. This is because flow of air separates from the wings,forming turbulent eddies.