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 Andrew Parker January 11, 2002 09:21

Pressure distribution over an airfoil-help

Dear all

I am having a problem with the pressure distribution over the surface of an airfoil. I have my own experimental data for lift, drag, and pressure distribution. The flow over the airfoil is separated in real life, and I have it separated in fluent. I have the lift accurate and the drag accurate but the pressure distribution constructed through xy plots is well off.

I don't understand how the lift, and drag can be accurate but the pressure is wrong. I am plotting static pressure against the distance along he airfoil. Has anybody had this problem? What was the remedy? Do I need to use surface integrals to work out the pressure distribution? Could it be to with reference pressures? I have set the gauge pressure on the pressure outlet boundary to zero. The wind tunnel discharges to atmosphere so this is correct, or is it? The operating pressure is 1 atmosphere. But the reference location (0,0) happens to coincide with the leading edge of the airfoil, does this matter?

Need help, a lot of it please!!!

Cheers

Andy

 anony January 15, 2002 12:32

Re: Pressure distribution over an airfoil-help

I hope you might be looking at the pressure coefficient values rather than the static pressure values. Did the experimental xy plot has the nondimensional units, if so they are pressure coefficients.

Try out the pressure coefficients for xy plot.

 Andrew Parker January 15, 2002 13:11

Re: Pressure distribution over an airfoil-help

Thanks, but that's not the answer the experimental data is my own from a wind tunnel and all the pressure are just static.

Cheers anyway

Andy

 belldingding January 17, 2002 00:02

I also have this trouble.

if you know,please tell me.

 Lakshmanagouda. .G.patil February 13, 2002 12:51

Re: I also have this trouble.

just see whether you are using cell values or node values. try by changing the node values on and off in xy -plot good luck

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