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By Brian J. Cantwell
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Extra resources for Aircraft and Rocket Propulsion
The shock moves upstream toward the inlet throat, the exit stagnation pressure increases and the product P te A e remains constant. The minimum exit area that can be reached without unstarting the inlet flow is when the inlet shock is very close to the throat and the shock becomes vanishingly weak. At this condition the only mechanism for stagnation pressure loss is the heat addition across the burner. 9. 22) To a reasonable approximation the stagnation loss across the burner can be neglected and we can take P te ≅ P t0 .
12) for a turbofan engine with two independent streams. Suppose 5% of the air from the high pressure compressor is to be used to power aircraft systems. What would be the appropriate thrust formula? Problem 3 - Consider the flow through a turbojet. 63) The enthalpy rise across the compressor is equal to the enthalpy decrease across the turbine. 63) can also be written ( m˙ a + m˙ f )h t5 = m˙ a h t2 + m˙ f h f . 64) The inlet and nozzle are usually assumed to operate adiabatically. 19). 1 RAMJET FLOW FIELD Before we begin to analyze the ramjet cycle we will consider an example that can help us understand how the flow through a ramjet comes about.
5 and e. 7054 . 004 . 2316 . 494 . 72 . 0724 State II - Now increase the inlet throat area to the point where the inlet unchokes. As the inlet throat area is increased the Mach number at station 3 will remain the same since it is determined by the choking at the nozzle exit and the fixed enthalpy rise across the burner. 5 is fixed by the loss across the external shock. 64). 64) is maintained and the inlet shock moves to the left increasing P te . 5 and the nozzle exit is across the burner.