F

Wf fuel

where:

TOGW = takeoff gross weight

empty operational weight empty

O/F = oxidizer to fuel ratio

WR = TOGW/OWE = weight ratio = mass ratio

So the weight ratio, hence the takeoff gross weight, is a direct result of the propellant weight with respect to the operational weight empty (OWE). The propellant weight is a direct function of the oxidizer to fuel ratio (O/F). In Figure 3.4 the mass ratio is a function of the carried oxidizer to fuel ratio. Note that in Figure 3.3 the mass ratio curve is essentially continuous, with an abrupt decrease at about Mach 5. In Figure 3.4 the oxidizer to fuel ratio is essentially constant for the rocket-derived

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