Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion

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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion ( comparison-concepts-classic-jet-propulsion-turbo-electric-pr )

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Table 4.3 A320 data for take-off distance (Nita 2013) 38 Parameter Take-off field length 𝑆 Factor π‘˜ Max. lift coefficient for take-off 𝐢 , , Value 1767.84 π‘š 2.25 π‘š β„π‘˜π‘” 2.24 4.2.3 Second Segment and Missed Approach 𝐸= 𝐢, (4.6) (4.7) 𝐢,+𝐢, πœ‹βˆ™π΄βˆ™π‘’ Table 4.4 Parameter Aspect Ratio 𝐴 Number of engines 𝑛 Climb angle (second segment) 𝑠𝑖𝑛𝛾 Climb angle (missed approach) 𝑠𝑖𝑛𝛾 𝑃, = 𝑛 βˆ™ 1+π‘ π‘–π‘›π›Ύβˆ™π‘‰βˆ™π‘” π‘šπ‘›βˆ’1πΈπœ‚, The aviation authorities have specific certification regulation for the climb gradient after the landing gear is fully retracted. The portion of the climb between the retraction of landing gear and flaps is known as second segment. They differ with the number of engines the aircraft is equipped with. The glide ratio in take-off configuration (𝐸 ) is calculated using the profile drag (𝐢 , ) and induced drag. The induced drag depends on the lift coefficient (𝐢 , ), Aspect ratio (𝐴), and the Oswald efficiency factor (𝑒). The power to weight ratio at take-off configu- ration is calculated using (4.7), where the number of engines (𝑛 ) play a significant role. 𝑉 is the take-off safety speed. A320 data for second segment and missed approach (Nita 2013) Value 9.5 m 2 and 4 0.024 0.021 When an aircraft landing is aborted, the aircraft is required to climb immediately for a second approach. The drag is higher compared to second segment climb since the landing gear is ful- ly extended. The equation for calculating the power to ratio for this configuration changes as seen in (4.8). 𝑃, = 𝑛 βˆ™1+π‘ π‘–π‘›π›Ύβˆ™π‘š βˆ™π‘‰βˆ™π‘” (4.8) π‘šπ‘›βˆ’1πΈπ‘šπœ‚,

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