Hi there,
My simulation involves looking at the stresses that a simple NACA airfoil withstands during flight.
I have generated an equation for the Coefficient of pressure. When I enter this into the variable pressure function area, it generates a plot thats very close to my Cp vs. x.
The only issue I am having now is that the simulation gives me extremely high readings. My question is, does anyone have any idea how the variable pressure works?
eg. If i have an x^2 varaible pressure along the flat plate, does each cross sectional piece see an pressure distribution of x^2 and then do all the pressures compound? or does it spread the pressure across the entire span of the plate?
Thanks
-T
Hi T-
Are the reactions correct, as in equaling the expected lift and drag? ("Results Contours > Other Results > Reactions > Reaction Force (Negative)")
To answer your question, the pressure is applied to each element face on the surface(s) that you select. As a confirmation, the title bar of the dialog indicates how many surfaces are selected. The calculation is something like this:
The math may be more complex that this simple example.
Right, thats what I thought.
I think I've debugged the issue. Currently, the Top surface is working fine and producing reasonable reaction forces on the airfoil. The issue I am having now is the lower surface. Its producing a force of 3.7kN.
Are there issues with using negative pressures?