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Altimeter — Manual 6.3 Altitude Derivative
p = p
0
"
T
0
+ T
′
0
·
z
T
0
#
− g
0
RT
′
0
(1)
p = p
1
exp
"
−
g
0
( z
−
z
1
)
RT
1
#
(2)
The equations converts geopotential altitude into pressure. Here z
means geopotential altitude, g
0
= 9 . 806645 m / s
2
is gravity constant,
R = 287 . 0528 N
·
m / kg
·
K. is gas constant for dry air, p
0
= 1013 . 25
hPa is standard pressure at sea level, p
1
= 226 . 321 hPa is standard
pressure at throposphere/thropopause limit, z 1 = 11000 m is geopo-
tential altitude of the limit, T
0
= 288 . 15 K is temperature at sea
level, T
1
= 216 . 65 K is temperature at limit and T
′
0
=
−
0 . 0065 K / m
is temperature gradient in throposphere.
Besides the equations given below, their inverse and derivatives of
inverse are also used.
6.3 Altitude Derivative
Altitude calculated from pressure is numerically derived to get rate
of altitude change – vertical speed. The derivative is mathematically
correct and as such does not introduce any error.
We are using
multiple point numerical derivation.
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