Aerodynamic Design of Transport Aircraft by E. Obert

By E. Obert

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For that case certain climb requirements must be met. Consequently the aircraft must be equipped with a minimum of two engines. A 2-engined aircraft must be able to continue the take-off after an engine failure on one engine, or 50% of the installed power. 4%. 2% . From the above it can be concluded that the everyday climb performance (with all engines operational) of a 2-engined aircraft will be considerably better than the performance of a 4-engined aircraft. This is an important factor when considering the noise characteristics of a particular aircraft from a certification point of view.

15 - Landing profile. Source: AGARD CP-365, paper no. 9 To illustrate the importance of an accurate estimation of the coefficients of an aircraft the effect of the lift coefficient on the weight and the take-off and landing field lengths are shown in figures 4-16 and 4-17. For a certain flap setting the weight-versus-field-length plots are limited by the WAT limit. 2 and has an available take-off field length of 10000 ft leading to a maximum take-off weight MTOW = 400,000 lb. 1. This then leads to a maximum take-off weight MTOW = 380,000 lb, a reduction of about 5%.

17 - Landing performance. 26 present some further information that should be of use for the estimation of the take-off and landing performance. 18 - Basic take-off framework. Source: AGARD LS-56, paper no. 19 - Engine thrust decay with speed. Source: AGARD LS-56, paper no. 21 - Take-off ground run. Source: AGARD LS-56, paper no. 20 - Take-off distance to screen. Source: AGARD LS-56, paper no. 22 - Take-off flare-up. Source: AGARD LS-56, paper no. 23 - Basic landing framework. Source: AGARD LS-56, paper no.

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