Question

1. (40) Consider a F-16 fighter jet flying at 40,000 ft (Pa,= 17.2kPa,7a -51°C, Ka = 1.4, Ra = 287 J/kgK) while traveling at subsonic speed. The gases from the engine can be considered as ideal gas with x = 1.33, R = 287 px. Now suppose the pilot needs to rapidly accelerate so that he/she calls for maximum thrust. A number of things will happen simultaneously as the throttle is increased: a. The engine rotational speed increases so that the mass flow rate increases to its maximum value of 122.5 kg/s b. Fuel begins flowing to the afterburner and is ignited there. Assume the stagnation pressure in the afterburner (AB) is constant at 289.6 kPa and velocity in the AB is 610 m/s. Ma C. With the AB operating, the stagnation temperature out of the AB and into the nozzle increases to T, = 1950°C) d. the nozzle is reconfigured to a converging-diverging (CD) nozzle. Determine the nozzle shape by specifying the inlet (1), throat (*), and outlet (2) diameter assuming May = 2.3. Be sure to carefully attach the appropriate subscripts to all quantities you are calculating.

Answer 1

Alhtud: 400 00 ft 17.2kPaT -5i'c 4 Ra a3/k Ergioe g 33 R - d/k ME122. Dfushuna, , k Cpe 610 m/ Mags &.3 ope 1450'c మ3 Conwuyut Biuyund A, At - 2.S04 Aj F8.35 669.53am AP O.2I439 Ax 0.2143 At A. 17.2 FO.21439 989-6 3.6017 AH