sweepback, and Mach number would deter- 
mine the sensitivity of the surface to changes 
in angle of attack. It should be appreciated 
that the flow at the horizontal tail is not of 
the same flow direction or dynamic pressure as 
the free stream. Due to the wing wake, fuse- 
lage boundary layer, and power effects, the q 
at the horizontal tail may be greatfy different 
from the 4 of the free stream. In most in- 
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