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.?