# 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.

Asked on 27th January 2022 in
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$