Question: I want to use 2 - d , steady source panel method to find the aerodynamic properties: C _ ij , phi _ ij ,

I want to use 2-d, steady source panel method to find the aerodynamic properties: C_ij, phi_ij, Vt_i, Cp_i, and delta s_j. I provided the equation sheet I used and my values for r_ij and cp_i. I want my values to be verified for N=4 panels and AOA -5 degrees for a NACA SC(2)0714 airfoil. Please show all calculations.
I want to use 2 - d , steady source panel method

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