Find the Mach number when an airplane is flying at 900 kmph through still air having a pressure of 8.0 N/cm^2 and temperature $-15^o$ C. Take k = 1.4 and R = 287 J/kg K. Calculate the pressure,temperature and density of the air at the stagnation point on the nose of the plane.

Stagnation Properties of a fluid is defined as "When a flowing fluid past an immersed body, and at a point on the boy if the resultant velocity becomes zero, then the values of pressure, temperature and density at that point are called as stagnation properties.

• That point is called …