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┣━╋━╋━╋━╋━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┣━╋━╋━╋━╋━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┣━╋━╋━╋━╋━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┗━┻━┻━┻━┻━┻━┻━┻━┻━┻━┻━┻━┛
where
                        by .
                       2ri   .
Fig.3.75   Empirical parameterk as a function ofbyl2ri (Ret:l).
Cyp.v = -ka, (1+ gdp)  7, ( SS )                           (3.303)
    Yv
 Cy.V = qS
CV.v = a~p
(3.304)
(3.305)
Here Yy is ffie side force on the vertical tail.
    The parameter k is given in Fig. 3.75 as a funcLion of by/2ri, where bu is the
vertical tail span measured up to the fuselage centerline and ri is the average
radius of the fuselage sections underneath the vertical tail. Furthermore, Su is
the theoretical vertical tail area (up to the fuselage centerline), a is the induced
 sidewash angle at the vertical tail, and Oy is the dynamic pressure ratio at the vertical
 tail. The sidewash, counterpart of downwash in horizontal plane,is mainly induced
by the forward sections of the fuselage as shown schematically in Fig. 3.76.
   The combined sidewash and dynamic pressure ratio term is gi\ren by the fol-
lowing empirical relation:l
        rr,d_i 3.06S,,]S +0.4zw+0.0009A  (3.306)
(1+  ;t3)  lu  = 0.724 + ~+~os Ac/4 + d fmax  .
where dj.n&Tr is the maximum fuselage depth, A the wing aspect ratio, Ac/4 is the

274            PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
V sin ( p+d )
Vsin p
al TaiL
Fig.3.76   Schematicillustrahon offuselage sidewashntverticaltail.
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
275
                                                                           
                                                                           
                                                                           
                                                                           
　
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