Consider the forebody, intake and the combustor for a conceptual scramjet engine shown in Fig. 7.11. The freestream conditions are M = 5, P_∞ = 830N/m² and T_∞ = 230 K. The ramp angles are 5◦, 10◦ and 15◦ from the horizontal. The engine uses kerosene fuel (calorific value = 45 MJ/kg). The air-fuel ratio on a mass basis is 80. The cross-section at the intake entrance is 920mm x 250mm and at combustor entrance 920mm x 85mm. Determine (a) the mass flow rate through the engine and (b) the Mach number, stagnation pressure recovery at the combustor inlet and outlet.

Sketc.h the process undergone by the fluid on a T-s diagram indicating all the static and stagnation states clearly. Assume critical mode of operation. Ignore expansion of the flow around the corner at the entry to the combustor.

Transcribed Image Text:

ramps (Forebody) Fig. 7.11 Illustration of a scramjet engine Intake Combustor