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Consider an aircraft with the following take-off specification: 

• Take-off field length = 1.9 km
• C_Lmax (at take-off) = 2.03

• Throttle setting = 98%
• Weight at take-off = 0.97 MTOW
• Ambient density = 0.954 ISA sea-level value (you'll need to go to the Working sheet here)

Q1 Calculate the Tsls/MTOW required to meet this take-off constraint at a design wing loading (MTOW/Sref) of 9,000 Pa. Give your answer to 3 d.p..

At landing conditions, the following specifications apply: 

• Landing field length = TOFL / 1.5 (TOFL as before)

• Landing C_Lmax = 2.3
• Weight at landing = MLW (using usual correlation with range = 5169 nm)
• Landing constant 'B' = 0.72
• Ambient density = 0.956 ISA sea-level value

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At landing conditions, the following specifications apply: 

• Landing field length = TOFL / 1.5 (TOFL as before)

• Landing C_Lmax = 2.3
• Weight at landing = MLW (using usual correlation with range = 5169 nm)
• Landing constant 'B' = 0.72
• Ambient density = 0.956 ISA sea-level value

Q3 Calculate, to the nearest 10 Pa, the maximum wing loading (MTOW/Sref, in Pa) which will still satisfy the LFL constraint.

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Recap:

Consider an aircraft with the following take-off specification: 

• Take-off field length = 2.8 km
• C_Lmax (at take-off) = 1.96

• Throttle setting = 98%
• Weight at take-off = 0.97 MTOW
• Ambient density = 0.964 ISA sea-level value

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Consider an aircraft with the following take-off specification: 

• Take-off field length = 2.8 km
• C_Lmax (at take-off) = 1.96

• Throttle setting = 98%
• Weight at take-off = 0.97 MTOW
• Ambient density = 0.964 ISA sea-level value (you'll need to go to the Working sheet here)

Q1 Calculate the Tsls/MTOW required to meet this take-off constraint at a design wing loading (MTOW/Sref) of 7,000 Pa. Give your answer to 3 d.p..

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Consider an aircraft with the following aerodynamic & mission specification: 

• CD0 = 0.0166; k = 1.23; AR = 9.4

• Cruise Mach = 0.81 at 37,000 ft

• Throttle setting 72%

• Cruise weight = 0.96 % MTOW

• Residual rate of climb allowance = 2.5 m/s

Answer the following three questions in turn:

Q1 What is the density of the atmosphere at the cruise altitude, in kg/m³

, to 4 d.p.?

Recap:

Consider a twin-engined aircraft with the following specification: 

• Basic aerodynamic performance C_D0 = 0.0178; k = 1.21; AR = 8.3;
• Take-off flap configuration: C_Lmax = 2.05; CD increment = 0.0110;
• Air speed during 2nd segment climb, V2 = 1.15 x stall speed
• The aircraft takes off at 0.90 MTOW
• Throttle setting during climb = 76%

• Minimum climb gradient = 1.7 %
• The local air density is 0.965 of the ISA sea-level value

Q4 What is the value of CD0 during 2nd segment climb, to 4 d.p.?

Q3 If the aircraft takes off at 0.90 MTOW and the local air density is 0.965 of the ISA sea-level value (you'll need to enter this directly into the Working sheet) , calculate the required Tsls/MTOW (to 3 d.p.) to achieve the climb performance specified above, at 76% throttle and with one engine inoperative.

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Consider a twin-engined aircraft with the following specification: 

• Basic aerodynamic performance C_D0 = 0.0178; k = 1.21; AR = 8.3; 
• Take-off flap configuration: C_Lmax = 2.05; CD increment = 0.0110;
• Air speed during 2nd segment climb, V2 = 1.15 x stall speed
• Throttle setting = 76%
• Minimum climb gradient = 1.7%

Answer the following three questions in turn:

Q1 What is the value CL during 2nd segment climb, to 3 d.p.?

Q4 What is the weight factor (i.e. W/MTOW) during 2nd segment climb, to 3 d.p.?