At a point in the flow over an F-15 high-performance fighter airplane, the pressure, temperature, and Mach number are \(1890 \mathrm{lb} / \mathrm{ft}^{2}, 450^{\circ} \mathrm{R}\), and 1.5 , respectively. At this point, calculate \(T_{o}, p_{o}, T^{*}, p^{*}\), and the flow velocity.