text: The contribution of the wing tb %tatic direc- 
  tional stability 
  is tisually small: The swept 
  wing provides a stable contribution’depending 
  on the amount of sweepback but the contribu- 
  tion is relatively weak when compared with 
  other components. 
  :. 
  The contribution of the fuselage and nacelles 
  
  is of primary importance since these compo- 
  nents furnish 
  in- 
  fluence. The contribution of the fuselage and 
  nacelles is similar 
  to the longitudinal case 
  the exception that there is no large in- 
  with 
  fluence of the induced flow field of the wing. 
  The subsonic center of pressure of the fuselage 
  will be located at or forward of the quarter- 
  length point and, since the airplane c.g. is 
  usually considerably aft of 
  the 
  fuselage contribution will be destabilizing. 
  However, at large angles of sideslip the large 
  destabilizing contribution of the fuselage di- 
  minishes which is some relief to the problem 
  of maintaining directional stability at large 
  displacements. The supersonic pressure,. dis- 
  tribution on the body provides a relatively  The contribution of the direct and indirect 
  is 
  power effects to static directional stability 
  greatest for 
  the propeller powered airplane 
  and usually slight for the jet powered airplane. 
  In either case, the general effect of power is 