Consider an airfoil flying at zero angle of attack. At low speeds (left(M_{infty} <0.2 ight)), the minimum

Consider an airfoil flying at zero angle of attack. At low speeds \(\left(M_{\infty}<0.2\right)\), the minimum pressure coefficient at a particular location on the airfoil is \(\sim 0.8\). Please find the airfoil's critical Mach number.