Tail Stability Known: Aircraft are inherently unstable

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Presentation transcript:

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

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

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

Unknown Parameters Xcg Lt Unknown Parameters Xcg Lt

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

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

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