NACA 0012 Different Angles of Attack

Arvind · January 27, 2010, 23:54

Hi All,

I want to perform flow simulations over NACA 0012 at different angles of attack. The method i followed is as below

X component of velocity, u = V cos(alpha)
Y component of velocity, v = V sin(alpha)

where alpha is the desired Angle of Attack.
I gave this conditions of velocities in the Inlet boundary condition which i have modelled as the left vertical plane .

Is this method correct??????

Attesz · January 28, 2010, 07:43

Send a picture about your domain with the boundaries marked. What are the other boundary conditions "above" and "under" the airfoil?

Arvind · January 28, 2010, 08:45

Hi Attila,

Here is the picture of my domain

I have given the velocity condition for inlet and pressure for both outlet and opening.

Inlet:

u = V cos(alpha)
v = V sin(alpha)
w = 0

Outlet & opening:

Static pressure: sea level

Attesz · January 28, 2010, 08:48

I can't find the picture...

Arvind · January 28, 2010, 08:52

Hey am very sorry it didnt attach it says it exceeds de memory.....am jus searching hw to reduce its size.......please don mind

Arvind · January 28, 2010, 09:06

I hav attached a word file which contains de domain pis.....

Attesz · January 28, 2010, 11:50

your settings are not so correct, you have better to use boundary conditions like in attached img.set the round inlet with velocity components, and the outlet to opening with static pressure, or set your inlet and opening boundaries to one opening with velocity, so you don't have to modify the geometry.

good luck

Attesz

Arvind · January 28, 2010, 23:55

Hi Attila,

Thnx a lot for ur help. I have never tried a boundary like u hav shown. I wil work on that and let u know if i find any difficulties.

mct90 · January 6, 2013, 16:27

Quote:

Originally Posted by Attesz

your settings are not so correct, you have better to use boundary conditions like in attached img.set the round inlet with velocity components, and the outlet to opening with static pressure, or set your inlet and opening boundaries to one opening with velocity, so you don't have to modify the geometry.

good luck

Attesz

Hi Attesz; can you upload the picture if you have it still, please?

N.veeraprasad · March 18, 2014, 01:14

I am doing project on naca 0012 airfoil. I am completing my model in 3-D but i have doubt is how to take domine sizes. please suggest me.

ghorrocks · March 18, 2014, 16:43

You should do a sensitivity analysis to find out how close your boundaries should be. Is this what you are asking?

January 27, 2010, 23:54	NACA 0012 Different Angles of Attack	#1
Arvind New Member Arvind Join Date: Mar 2009 Posts: 15 Rep Power: 16	Hi All, I want to perform flow simulations over NACA 0012 at different angles of attack. The method i followed is as below X component of velocity, u = V cos(alpha) Y component of velocity, v = V sin(alpha) where alpha is the desired Angle of Attack. I gave this conditions of velocities in the Inlet boundary condition which i have modelled as the left vertical plane . Is this method correct??????

January 28, 2010, 11:50		#7
Attesz Senior Member Attesz Join Date: Mar 2009 Location: Munich Posts: 368 Rep Power: 16	your settings are not so correct, you have better to use boundary conditions like in attached img.set the round inlet with velocity components, and the outlet to opening with static pressure, or set your inlet and opening boundaries to one opening with velocity, so you don't have to modify the geometry. good luck Attesz Last edited by Attesz; January 28, 2010 at 13:34.

March 18, 2014, 01:14	Naca 0012 airfoil domine size in 3-D	#10
N.veeraprasad New Member Nagari.Veeraprasad Join Date: Mar 2014 Posts: 1 Rep Power: 0	I am doing project on naca 0012 airfoil. I am completing my model in 3-D but i have doubt is how to take domine sizes. please suggest me.

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January 28, 2010, 07:43		#2
Attesz Senior Member Attesz Join Date: Mar 2009 Location: Munich Posts: 368 Rep Power: 16	Send a picture about your domain with the boundaries marked. What are the other boundary conditions "above" and "under" the airfoil?

January 28, 2010, 08:45		#3
Arvind New Member Arvind Join Date: Mar 2009 Posts: 15 Rep Power: 16	Hi Attila, Here is the picture of my domain I have given the velocity condition for inlet and pressure for both outlet and opening. Inlet: u = V cos(alpha) v = V sin(alpha) w = 0 Outlet & opening: Static pressure: sea level

January 28, 2010, 08:48		#4
Attesz Senior Member Attesz Join Date: Mar 2009 Location: Munich Posts: 368 Rep Power: 16	I can't find the picture...

January 28, 2010, 08:52		#5
Arvind New Member Arvind Join Date: Mar 2009 Posts: 15 Rep Power: 16	Hey am very sorry it didnt attach it says it exceeds de memory.....am jus searching hw to reduce its size.......please don mind

January 28, 2010, 23:55		#8
Arvind New Member Arvind Join Date: Mar 2009 Posts: 15 Rep Power: 16	Hi Attila, Thnx a lot for ur help. I have never tried a boundary like u hav shown. I wil work on that and let u know if i find any difficulties.

March 18, 2014, 16:43		#11
ghorrocks Super Moderator Glenn Horrocks Join Date: Mar 2009 Location: Sydney, Australia Posts: 17,324 Rep Power: 138	You should do a sensitivity analysis to find out how close your boundaries should be. Is this what you are asking?