[winglet]

hi All,

I am int interested to see flow behavior on wings and wing with winglet.

I have the following test conditions :

Stagnation temperature =322 K
dynamic pressure : 41KN/M^2
Mach = 0.8
Re =17 million per unit length.

with these test conditions ,how to apply BC in CFX Pre?

[ghorrocks]

Hi,

Look up the definition of all these terms. Then solve a simultaneous set of equations to determine what they mean in terms of pressure, velocity, density etc.

Then you apply the boundary in CFX-Pre, probably in terms of velocity and temperature inlet and pressure outlet.

Glenn Horrocks

[winglet]

Hi ghorrocks,

Thanks for your reply.
I able to caalculate velocity and temperature from the availble data. I am not sure on exit boundary condition,because the data does not provide any thing on outlet.
can I use relative static pressure as zero at outlet?

[ghorrocks]

Hi,

The exit pressure will be whatever the ambient pressure is. Unless you know otherwise then I would guess 1 atm absolute. You would then use 1 atm as your reference pressure and set the exit pressure to 0 gauge pressure.

Glenn Horrocks

[winglet]

Originally Posted by ghorrocks

Hi,

The exit pressure will be whatever the ambient pressure is. Unless you know otherwise then I would guess 1 atm absolute. You would then use 1 atm as your reference pressure and set the exit pressure to 0 gauge pressure.

Glenn Horrocks

Thanks. I set up CFX run today .Let me see how it will run.