Hydraulics

Download PDF by Brian J. Cantwell: Aircraft and Rocket Propulsion

By Brian J. Cantwell

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Sample text

We have already studied those effects fairly thoroughly. In addition there are stagnation pressure losses due to burner drag and skin friction losses in the inlet and nozzle where the Mach numbers tend to be quite high. A reasonable rule of thumb is that the stagnation pressure losses due to burner drag are comparable to the losses due to heat addition. 6 RAMJET CONTROL Let’s examine what happens when we apply some control to the ramjet. The two main control mechanisms at our disposal are the fuel flow and the nozzle exit area.

981 . 0725. The fact that the Mach number at station 3 is higher than this value implies that there is a shock in the diverging part of the inlet and the inlet throat Mach number is equal to one. 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.

We have already studied those effects fairly thoroughly. In addition there are stagnation pressure losses due to burner drag and skin friction losses in the inlet and nozzle where the Mach numbers tend to be quite high. A reasonable rule of thumb is that the stagnation pressure losses due to burner drag are comparable to the losses due to heat addition. 6 RAMJET CONTROL Let’s examine what happens when we apply some control to the ramjet. The two main control mechanisms at our disposal are the fuel flow and the nozzle exit area.

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Aircraft and Rocket Propulsion by Brian J. Cantwell


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