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 Aerodynamics.
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    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,\[C_{p}=\frac{2\left ( 0.0873 \right )}{\sqrt{\left ( 2.5 \right )^{2}-1}}=0.0762\]

    Answered on 28th January 2022.
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