I am trying to make a wing where slats automatically deploy once it hits a higher angle of attack, let's say right before stall. I need to roughly estimate the forces and moments acting on the undeployed slat.
Here is a sample airfoil with the pressure distribution superimposed:
I plan to operate at a Reynolds number of 100,000 at stall speed, and the preliminary dimensions for the slat position are 10% for the width, 1.5% for the depth and 2% for the gap, all in chord percentage. Refere to the image below for the definition of the dimensions:
Source: Effect of Slot Span on Wing Performance, J.Granizo
I think the next step is to use the following equations for the slat alone:
However, I only know the pressure and friction coefficients on the top surface (marked in red line). Do I assume that the entire bottom surface (marked in blue line) is at atmospheric/freestream pressure?
A point in the right direction would be appreciated.