Mecanica De Materiales

rnoverneut w,H cause an overswing of the airplane past the equilibrium side slip angle. The magnifieation of the side slip, Kp, will be approximately 1.4 to1.6. In this condition the rudder is eonsidered to be dcflcct-
ed. The tailload equation beeomes

Yv/ = l( 6. C"¡¡)Vl KtJ Pu - e "óy y] q -= (3.6.16)(overswing force)
(1) Aileron roll case
In this condition the ailerons are considered to
be suddenly deflected whilc the rudder is held neutral. Theequations for tail load are similar to thc ones shown previously for rudder deflection, In this case, the side slip anglc is being caused by the ailerons andthe airplane rolling velocity,
Thc cquilibrium side slip angle is

pb + C ó
"p 2 V noa o









(3)
However, with thefailure of a turhinc engine, a largc amount of drag on the failed engine will be experienced. Time history of the enginc thrust and drag ís shown in fíg.3.6.10.
This asyrnrnetric thrust will induce large side
slip angles. Because of the rapid application of this force, a considerahle magnification of theside slip angle wiU OCCUL
Distribution of load on vertical tail
For spanwise variation of airload, a plan form distribution is usually satisfactory.Chordwise pressure distributions for subsonic speeds will as- sume the shapes as shown in Fig. 3A 11.



Rudder hinge

l_!
{JII = ---- -_.
(3.6.17)

O~--------C-h-o-rd----------_'I--~~--~Óy-O


1.0

Thc numerator terms can be approximatcd

vcry roughly by Ct . The...