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Problem $05\mathrm{.}027-$ Airfoil lift coefficient of a Lockheed F$-104-$ DEPENDENT MULTI$-$PART PROBLEM ASSIGN ALL THE PARTS

The airfoil on the Lockheed F$-104$ straight$-$wing supersonic fighter is a thin, symmetric airfoil with a thickness ratio of $3\mathrm{.}5$ percent. Consider this airfoil in a flow at an angle of attack of $\backslash (6^\{\backslash$circ$\}\backslash ).$ The incompressible lift coefficient for the airfoil is approximated by $\backslash ($ q$=2\backslash$pi $\backslash$alpha $\backslash ),$ where $\backslash (\backslash$alpha $\backslash )$ is the angle of attack in radians.

NOTE: This is a multi$-$part question. Once an answer is submitted, you will be unable to return to this part.

Problem $05\mathrm{.}027.$c $-$ Estimate airfoil lift coefficient

Estimate the airfoil lift coefficient for $\backslash ($ M$=2\backslash ).$

The airfoil lift coefficient for $\backslash ($ M$=2\backslash )$ is