Consider a diamond-shaped airfoil such as that sketched in Fig. 4.35. The half-angle is \(\varepsilon\), thickness is \(t\), and chord is \(c\). For supersonic flow, use linearized theory to derive the following expression for \(C_{D}\) at \(\alpha=0\) :

\[C_{D}=\frac{4}{\sqrt{M_{\infty}^{2}-1}}\left(\frac{t}{c}\right)^{2}\]

Figure 4.35:

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P3