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 14 compression corner then point (2) to (3) across a 33 expansion corner. (2) (1) J 1 (3) (a) Describe the phenomena that will occur at the nose of the aircraft given the nose angle is 59 from the direction of the flow. State evidence to support your description. (b) The aircraft is fitted with a pitot tube which is measuring 5.99 10 N/m in region 1. The aircraft is at an altitude of 35km where the following can be assumed about the flow properties: temperature = 246.09K, atmospheric pressure = 583 Pa, and density = 0.00826 kg/m. 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)