A subsonic airplane is flying at a 9000 meter altitude where the atmospheric conditions are 30.8 kPa and 240 K. A Pitot static probe measures the absolute difference between the static and stagnation pressures to be 20 kPa. Assume air is ideal gas and a constant specific heat and use the properties at room temperature,

Determine

(a) the flight Mach number,
(b) the speed of the airplane,
(c) the stagnation temperature on the leading edge of the wing.