1. B2(a) Calculate the lift coefficient of the aircraft.
2. B2(b) Calculate the lift coefficient of the tailplane (Assume dynamic pressure is same at tail and wing)
3. B2(c) Calculate the lift force produced by the tailplane.
4. B2(d) Determine angle of attack of the tailplane with the tab undeflected.
5. B2(e) Determine the elevator angle required to trim the aircraft with the tab undeflected.
6. B2(f) Determine the stick position required to trim the aircraft with the tab undeflected.

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