Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow at an angle of attack of \(5^{^{\circ}}\), using linearized theory.
Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow at an angle of attack of \(5^{^{\circ}}\), using linearized theory.
Here, \[\alpha = 5^{\circ}=0.0873\,rad,\, M = 2.5\]From linearized theory, for a flat plate at an angle of attack \[c_{l}=\frac{4\alpha }{\sqrt{M_{\infty}^{2}-1}}\]Therefore, \[c_{l}=\frac{4\left ( 0.0873 \right )}{\sqrt{\left ( 2.5 \right )^{2}-1}}=0.1524\]\[c_{d}=\frac{4\alpha ^{2}}{\sqrt{M_{\infty}^{2}-1}}\]Therefore, \[c_{d}=\frac{4\left ( 0.0873 \right )^{2}}{\sqrt{\left ( 2.5 \right )^{2}-1}}=0.0133\]\[C_{p}=\frac{2\theta}{\sqrt{M_{\infty}^{2}-1}}\]Therefore,\[C_{p}=\frac{2\left ( 0.0873 \right )}{\sqrt{\left ( 2.5 \right )^{2}-1}}=0.0762\]
