Determine the Mach number when an aero plane is flying at 800 km/hr. through still air having pressure of 90 kPa and temperature 25C. Take k = 1.4 and R = 287 J/kgK. At the stagnation point of the plane, i.e. at the nose of the plane, calculate (i) pressure, (ii) temperature, and (iii) density. To k-1 T=1+ M - 2 Po = (1 + k 1 1 Po P 2 M k M (k-1) 12) -(1+4) == 2