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wing quarter chord sweep, and zw is the vertical distance (measured parallel to the
 z axis) from wing root quarter chord point to the fuselage centerline, positive if the
wing is below the fuselage centerline. The lift-curve slope au of the vertical tail
can be obtained using the methods given in Section 3.3 using its effective aspect
ratio as given by the following expression:l
        Au.efir=(AA A,) 1+KH(AA  -1)]    (3.307)
 where Au(B)/Av is the ratio of the vertical tail aspect ratio in the presence of the
 body to that of the isolated vertical tail as given in Fig. 3.77. The parameters used
 in Fig. 3.77 are 1) bu, the vertical tail span measured up to the fuselage centerline;
 2) ri, fuselage depth in the region of vertical tail; and 3) Au, vertical tail taper
AV(B1
Av
STATIC STABfLITY AND CONTROL
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┃    ┃Av        ┃  --  ┃\   - ┃  ┃  ┃  ┃      ┃  ┃  ┃  ┃  ┃  ┃
┣━━╋━━┳━━╋━━━╋━━━╋━╋━╋━╋━━━╋━╋━╋━╋━╋━┫
┃    ┃s   ┃'~  ┃ --   ┃\     ┃~ ┃  ┃  ┃      ┃  ┃  ┃  ┃  ┃  ┃
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┃    ┃    ┃    ┃      ┃      ┃  ┃  ┃  ┃      ┃  ┃  ┃  ┃  ┃  ┃
┣━━╋━━╋━━╋━━━╋━━━╋━╋━╋━╋━━━╋━╋━╋━╋━╋━┫
┃    ┃//  ┃7   ┃      ┃      ┃~ ┃~ ┃~ ┃>~--  ┃  ┃  ┃  ┃  ┃  ┃
┃/   ┃7   ┃    ┃      ┃      ┃  ┃  ┃  ┃      ┃  ┃  ┃  ┃  ┃  ┃
　
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