Reynolds and Mach Number Consider a commercial airliner flying at a speed of 560mph (relative to the air) at an altitude of 30,000 feet. (a) Use the 1976 US Standard Atmosphere to determine the temperature, pressure, and density of air at this altitude. (b) Over a wide range of temperature, the dynamic viscosity of air follows the Sutherland Law, 0=(T0T)3/2T+ST0+S, where 0=1.716105Pas,T0=273K, and S=111K. Use this to determine the air viscosity at 30,000 feet. (c) With a mean molar mass of M=28.9g/mol, determine the Reynolds number and Mach number in flight. (d) Is this flow inviscid or viscous? Is this flow subsonic or supersonic? Qualitatively describe the differences between these flight regimes