Derivations are presented for the range of aircraft with gas-turbine propulsion systems, which cannot be characterized to have either constant specific fuel consumption or constant propulsive efficiency. The effects of different cruise techniques are investigated. It is found that for preliminary design purposes a very simple approximation of the fuel fraction can be used for all aircraft categories and various cruise techniques. This result has been used to compute the total mission and reserve fuel.
Initial Calculation of Range and Mission Fuel during Conceptual Design
1987
29 pages
Report
No indication
English
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