PART 6: Mass Model and Fuel Consumption
Loss of aircraft mass is assumed to be a consequence of fuel consumption only. The rate of mass loss is assumed to be directly proportional to engine thrust. Expressed mathematically, the mass model becomes,
 |
(6-1) |
where 
is a constant whose nominal value is 4x10-6 slugs/pounds-second, and 
is engine thrust. The instantaneous aircraft mass, 
, is obtained by integrating Equation 6-1 over time with the initial condition,
 |
(6-2) |
where 
is the mass of the fully loaded aircraft.
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