1. Tail Stability Known: Aircraft are inherently unstable
Tail balances the induced moments

2. Equations Used Mac = Mac + Wxcg –Clt(lt + xcg)
Clt = (aot/(1+(57.3aot/e1ARt))*( - L=0)
q = (1/2)V­­2

3. Known Parameters Unknown Parameters Free Stream Velocity Chord of wing
Plan form area of wing
Weight
Unknown Parameters
Xcg Lt

4. Unknown Parameters
Xcg Lt
Unknown Parameters
Xcg Lt

7. Determined Values Lt = 14 inches Xcg = 3 inches
Span of tail =1.16 feet

8. Comments Further tail is from cg, smaller tail size.
Incorrect values for tail size for ideal case
May be due to missing conversion factor
Investigation required

9. Future Work Full body moment balance Solution incorporating tolerances
Fuselage contributions
Weight balance of each component
Solution incorporating tolerances