Q7 Now set the RRC to zero and re-calculate the required Tsls/MTOW (to 3 d.p.) at a design wing loading of 6,000 Pa.

Recap:

Consider an aircraft with the following aerodynamic & mission specification: 

• CD0 = 0.0172; k = 1.18; AR = 9.7
• Cruise Mach = 0.88 at 38,000 ft
• Throttle setting 78%

• Cruise weight = 0.94 % MTOW
• Residual rate of climb allowance = 2.2 m/s

Q4 What is the cruise thrust factor (T/Tsls) at 38,000 ft, to 3 d.p.?

Q5 What is the dynamic pressure (at Mach 0.88, 38,000 ft), to the nearest Pascal?

Q3 Calculate the required Tsls/MTOW (to 3 d.p.) to satisfy this Cruise requirement at a design wing loading (MTOW/Sref) of 6,000 Pa

NOTE: DO NOT MOVE ON TO THE NEXT PAGE WITHOUT ATTEMPTING THESE THREE QUESTIONS!

Consider an aircraft with the following aerodynamic & mission specification: 

• CD0 = 0.0172; k = 1.18; AR = 9.7

• Cruise Mach = 0.88 at 38,000 ft

• Throttle setting 78%

• Cruise weight = 0.94 % MTOW

• Residual rate of climb allowance = 2.2 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.?

Q5 What is the dynamic pressure (at Mach 0.81, 37,000 ft), to the nearest Pascal?

Recap:

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

Q4 What is the cruise thrust factor (T/Tsls) at 37,000 ft, to 3 d.p.?

At landing conditions, the following specifications apply: 

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

• Landing C_Lmax = 2.7
• Weight at landing = MLW (using usual correlation with range = 6446 nm)
• Landing constant 'B' = 0.72
• Ambient density = 0.974 ISA sea-level value

DO NOT MOVE ON TO THE NEXT PAGE WITHOUT ATTEMPTING THIS QUESTION!

At landing conditions, the following specifications apply: 

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

• Landing C_Lmax = 2.7
• Weight at landing = MLW (using usual correlation with range = 6446 nm)
• Landing constant 'B' = 0.72
• Ambient density = 0.974 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.

DO NOT MOVE ON TO THE NEXT PAGE WITHOUT ATTEMPTING THIS QUESTION!

Recap:

Consider an aircraft with the following take-off specification: 

• Take-off field length = 3.0 km
• C_Lmax (at take-off) = 2.14

• Throttle setting = 98%
• Weight at take-off = 0.96 MTOW
• Ambient density = 0.954 ISA sea-level value