text: An additional factor for consideration is the 
  influence of the induced flow field of the wing. 
  As illustrated in figure 4.8, the upwash ahead 
  of the wing increases the destabilizing influence 
  from the portions of the fuselage and nacelles 
  ahead of the wing. The downwash behind 
  the wing reduces the destabilizing influence 
  from the portions of the fuselage and nacelles 
  aft of the wing. Hence, the location of the 
  fuselage and nacelles relative to the wing is 
  important in determining the contribution 
  to 
  stability. 
  
  Many factors influence the change in tail 
  lift which occurs with a change in airplane 
  angle of attack. The area of the horizontal 
  tail has the obvious effect that a large surface 
  would generate a large change in lift. 
  In a 
  similar manner, the change in tail lift would 
  depend on the slope of the lift curve for the 
  horizontal 
  taper, 
  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 
  In most in- 
  from the 4 of the free stream.  in supersonic flow 
  can develop lift of a magnitude which cannot 
  be neglected. When the body of revolution in 
  supersonic flow is given an angle of attack, a 
  pressure distribution typical of figure 4.8 is the 
  result. Since the center of pressure is well 
  forward, the body contributes a destabilizing 
  influence. AS is usual with supersonic con- 
  figurations, the fuselage and nacelles may be 
  quite large in comparison with 
  the wing area 
  and the contribution to stability may be large. 
  Interaction between the wing and fuselage and 
  
  The body of revolution 