Question: I want to use 2 - d , steady source panel method to find the aerodynamic properties: C _ ij , phi _ ij ,
I want to use d steady source panel method to find the aerodynamic properties: Cij phiij Vti Cpi and delta sj I provided the equation sheet I used and my values for rij and cpi I want my values to be verified for N panels and AOA degrees for a NACA SC airfoil. Please show all calculations.
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