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As this did not happen (at the time) the design was fuel efficient but expensive. The typical mission phases of an aircraft are: take-off , climb, cruise, descend and landing. 1) where V L SFC D = K R V = = = Range factor Constant Range Airspeed L D = SFC = W1 = W2 = Lift over drag ratio Specific fuel consumption Weight at start Weight at end 19 AERODYNAMIC DESIGN OF TRANSPORT AIRCRAFT In order to increase the range the airspeed could be increased. 85 is typical. For higher airspeeds flying becomes more expensive because of the high fuel consumption, highly swept wings become necessary and the aircraft becomes heavier which reduces the range.
8) Where ρ0 is the free stream air density, V0 is the free stream velocity, T is the static temperature and R is the universal gas constant. 5.
The increase in weight during the development had a “snowball effect”, a small increase in weight of some component resulted in a further increase in total weight and so on. The first aircraft was certificated at a MTOW of 710,000 lb, which is an increase of 29%. In general a good insight is required in projected economic and social development in the not-too-near future. Note that between the initial project definition and first aircraft delivery 5 to 7 years may pass after which the aircraft will have an operational life of at least 30 years.