Recap:

Consider a twin-engined aircraft with the following specification: 

• Basic aerodynamic performance C_D0 = 0.0168; k = 1.20; AR = 8.6;
• Take-off flap configuration: C_Lmax = 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.?