6. A stealth aircraft has a fuselage profile that can be simplified to the diagram below. The flow moves from point (1) to point (2) across a 18 compression corner then point (2) to (3) across a 25 expansion comer. (b) (c) (a) (a) Describe the phenomena that will occur at each corner under supersonic flow. Give details as to the general change to flow properties across each phenomena. (b) The aircraft is fitted with a pitot tube which is measuring 6.22 x 104 N/m. The aircraft is at an altitude of 20km. Calculate the velocity of the aircraft. (c) Assuming the Mach number from part (b) occurs at point (1) in the diagram, determine the Mach number and Pressure at: (i) Point (2) (ii) Point (3)