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EG2100 Engineering Design II - Aerospace (PRD1 A 2025/26)
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Q6 What is the thrust factor (Tclimb/Tsls) during 2nd segment climb, to 3 d.p.?
Recap:
Consider a twin-engined aircraft with the following specification:
- Basic aerodynamic performance CD0 = 0.0168; k = 1.20; AR = 8.6;
- Take-off flap configuration: CLmax = 2.00; CD increment = 0.0130;
- Air speed during 2nd segment climb, V2 = 1.15 x stall speed
- The aircraft takes off at 0.97 MTOW
- Throttle setting during climb = 75%
- Minimum climb gradient = 1.5 %
- The local air density is 0.962 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 0.97 MTOW and the local air density is 0.962 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 75% throttle and with one engine inoperative.
Q2 What is the value of D/L during 2nd segment climb, to 3 d.p.?
NOTE: DO NOT MOVE ON TO THE NEXT PAGE WITHOUT ATTEMPTING THESE THREE QUESTIONS!
Consider a twin-engined aircraft with the following specification:
- Basic aerodynamic performance CD0 = 0.0168; k = 1.20; AR = 8.6;
- Take-off flap configuration: CLmax = 2.00; CD increment = 0.0130;
- Air speed during 2nd segment climb, V2 = 1.15 x stall speed
- Throttle setting = 75%
- Minimum climb gradient = 1.5%
Answer the following three questions in turn:
Q1 What is the value CL during 2nd segment climb, to 3 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 9,000 Pa.
Q5 What is the dynamic pressure (at Mach 0.84, 34,000 ft), to the nearest Pascal?
Recap:
Consider an aircraft with the following aerodynamic & mission specification:
- CD0 = 0.0172; k = 1.23; AR = 7.6
- Cruise Mach = 0.84 at 34,000 ft
- Throttle setting 77%
- Cruise weight = 0.97 % MTOW
- Residual rate of climb allowance = 2.1 m/s
Q4 What is the cruise thrust factor (T/Tsls) at 34,000 ft, to 3 d.p.?
Q5 What is the dynamic pressure (at 214 kts, 1500 ft), to the nearest Pascal?
Recap:
Consider an aircraft with the following aerodynamic & mission specification:
- CD0 = 0.0181; k = 1.23; AR = 8.9
- Hold speed = 214 kts at 1500 ft
- Rate of turn = 3.6 deg/s
- Throttle setting 50%
Hold weight = 0.85 MTOW