Development of a Mass Estimating Relationship Database for ...

2.0 Tail
Reference: 6
Derived from: Boeing aircraft tail equations adjusted for Space Shuttle.
Options: Component inclusion.
The following three equations must be summed to find the total tail mass.
Space Shuttle
Comparison
-8%
0.244 0.0364
( S ( ) ) t
0. 8674
c b
M = 26.06
vert
M
tail
vert _ spar
=
fairing
c
tip
2S
vert
b
fairing
vert
vert
M
vert
tail
( .02499q
+ 1.7008 + ( 0.003695q
− 0. ) b )
M = S
3252
0
max
max
body
b body – Maximum width of the body
b vert – Span of tail or tip fins
c tip – Tip chord of vertical tail or wingtip fins
q max – Maximum dynamic pressure during flight
S fairing – Surface area of tail fairing
S vert – Total planform area of vertical tail or wingtip fins
(t/c) vert – Thickness to chord ratio of the vertical tail or wingtip fins
Georgia Institute of Technology 2-8