2 3 4 30 1 25° 5
The instrument fairing on an aircraft is shown below, consisting of a forward ramp at
30◦, a horizontal section, and a rear ramp at 25◦. During a flight in air at Mach 5.5,
the static pressure is 42.6 kPa and the static temperature is 250 K. An oblique shock
forms at the turn of the forward ramp, two expansion fans form at the front and rear of
the horizontal section, and a second oblique shock forms at the turn of the rear ramp.
(a) Calculate the Mach numbers and pressures at regions 2, 3, 4, and 5.
(b) Determine stagnation pressure ratio p05/p01.
(c) Tabulate the angles of all oblique shocks waves leading/trailing expansion waves relative to horizontal (not relative to flow angle).
Gamma = 1.4, R=287 J/kgK
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