change angle of attack in aerofoil
 

Hi, I would like to know if it is possible to change the angle of attack of an aerofoil in OpenFOAM. I've been told that it's possible in Fluent so I guess there must be something similar in OpenFOAM. Thanks!

Hi,

I am not an experienced user of OpenFOAM. But, I think It is just a matter of changing your B.Cs in the OpenFOAM.

Good luck

angle of attack
 

hi nicchani

Hi, yes it is possible to change the angle of attack of an aerofoil in OpenFOAM too like fluent. just change in the 0 directory there is file named called velocity "u", just change according to your velocity like 51*cos(2) along x direction and 51*sin(2) along y direction as u required for different angle of attacks ( example i have given 2 is the angle of attack) calculate from these cos and sin put those values in the file "u"....

ok, thanks to both of you for your help! I will try the sin and cos method :)

hey naveen,
why is 51 there in the equation ?

change angle of attack in aerofoil
 

dear deepaktbabu,

It is the velocity what you are taking from Mach number...just i have given velocity reference for mach number at 0.3...you can give ur velocity depends on ur mach number..

thank you :)

I am not quiet sure because one will be bigger and one will be lower for example the cos bit is bigger than the sin bit.......

Dear Naveen, when we have three element airfoil, we should add the angle of attack to deflection angle of each of them,e.g the main element has 0 degree angle and the flap(another element of three element airfoil) has 30 degree angle.
what should we write for liftDir and dragDir in controlDict according to their angles?

Angle of attack for LES in openfoam using pointwise mesh
 

/*--------------------------------*- C++ -*----------------------------------*\
========= |
\\ / F ield | OpenFOAM: The Open Source CFD Toolbox
\\ / O peration | Website: https://openfoam.org
\\ / A nd | Version: 8
\\/ M anipulation |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class volVectorField;
object U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [0 1 -1 0 0 0 0];

internalField uniform (0 0 0);

boundaryField
{
inlet
{
type turbulentInlet;
referenceField uniform (10 0 0);
fluctuationScale (0.02 0.01 0.01);
value uniform (10 0 0);
}

outlet
{
type inletOutlet;
inletValue uniform (0 0 0);
value uniform (0 0 0);
}

upperWall
{
type noSlip;
}

lowerWall
{
type noSlip;
}

frontAndBack
{
type empty;
}
}

// ************************************************** *********************** //
if this my u file should i put values ucos2 and usin2 for AOA=2? in the highlighted part only ?