Tranquillus, Analysis Data Item Vol. 2

c  k   f  r ,  r   cv 

The rudder span factor is obtained from Figure 8.51 with data from Figure 8.52 in Airplane Design Part VI and is a function of the rudder inboard and outboard stations and vertical tail taper ratio:

K b  K bO  K bi Where: K bO  f Or , v

  f 

Eqn.(11)

 , 

K bi Or v The correction factor for sectional rudder lift is obtained from Figure 8.15 in Airplane Design Part VI and is a function of the rudder chord to vertical tail chord ratio and the sectional lift curve slope to theoretical lift curve slope ratio:   cl  c a clW , M  0   f ,  cl  c w cl  Theory Theory   The theoretical vertical tail sectional lift curve slope at zero-Mach is given by:

C



lV M  0 Theory

t  2  5.0525   c v

Eqn.(12)

The lift effectiveness parameter is found from Figure 8.14 in Airplane Design Part VI and is a function of the rudder chord to vertical tail chord ratio and the thickness ratio of the vertical tail at the center of the rudder:  cr  t    ,    f  theory  cv  c  v  The “three dimensional rudder effectiveness parameter” is determined from Figure 8.53 in Airplane Design Part VI and is a function of the vertical tail aspect ratio, and rudder chord to vertical tail chord ratio:

c  l

  CL   Cl

Cr   f  ARv , eff C v 

Segment: Cy r

C y , Rudder

  

rad  1

1 2 3 4 5 6 7 n/a 0.1885 0.1906 0.1907 0.1999 0.2546 0.3335 n/a 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000

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