c$)$ The analysis is now extended to the flow past a symmetric

diamond aerofoil at a zero angle of attack, shown in figure

Q$2,$ with the same inlet conditions, semi$-$angles at the

leading and trailing edges of $12$ and a chord length of $1$ m $.$

Calculate the total drag per unit length in the spanwise

direction on the aerofoil.

Figure Q$2$: Flow past a symmetrical diamond$-$shaped aerofoil $($not to sc