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

Consider an aircraft with the following aerodynamic & mission specification: 

• CD0 = 0.0174; k = 1.20; AR = 7.4

• Cruise Mach = 0.86 at 34,000 ft

• Throttle setting 75%

• Cruise weight = 0.95 % MTOW

• Residual rate of climb allowance = 0.8 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.?

Q7 Now set the RRC to zero and re-calculate the required Tsls/MTOW (to 3 d.p.) at a design wing loading of 10,000 Pa.

Q6 What is the climb gradient for the given residual rate of climb and cruise speed, quoted in % and to 3 d.p.?

Q5 What is the dynamic pressure (at Mach 0.78, 34,000 ft), to the nearest Pascal?

Recap:

Consider an aircraft with the following aerodynamic & mission specification: 

• CD0 = 0.0173; k = 1.22; AR = 9.3
• Cruise Mach = 0.78 at 34,000 ft
• Throttle setting 75%

• Cruise weight = 0.96 % MTOW
• Residual rate of climb allowance = 2.0 m/s

Q4 What is the cruise thrust factor (T/Tsls) at 34,000 ft, to 3 d.p.?

Q3 Calculate the required Tsls/MTOW (to 3 d.p.) to satisfy this Cruise requirement at a design wing loading (MTOW/Sref) of 10,000 Pa

Q2 What is the speed of the aircraft at these  conditions, in m/s, to 1 d.p.?

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

Consider an aircraft with the following aerodynamic & mission specification: 

• CD0 = 0.0173; k = 1.22; AR = 9.3

• Cruise Mach = 0.78 at 34,000 ft

• Throttle setting 75%

• Cruise weight = 0.96 % MTOW

• Residual rate of climb allowance = 2.0 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.?