O

Builder's analysis No drag losses

15 20

Flight speed (kft/s)

Figure 4.19. System thermal integrated specific impulse.

At 2,000 R (1,111 K) the hydrogen specific impulse is 509 s, or better than a hydrogen/oxygen rocket. For a scramjet engine with an equivalence ratio greater than one, this can produce 30% or more of the engines net thrust [Novichkov, 1990]. Applying this approach and using Builder's Second Law, the impact of fuel temperature injected through Mach 3 nozzles in the combustor wall (Figure 4.19) can be assessed.

One measure of airbreathing engine performance is the energy conversion efficiency (0). The definition is:

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