Douglas A-4M - Descent; Maximum Range Descent

MAXIMUM RANGE DESCENT
NAVAIR 0 1·4 0AVM -}
PART 7
DESCENT
Graphical data are pr esen ted in figures 11-41 through
11 -43 for maximum range descent us ing idle thrust
and with speedbrakes closed, R ecom mended ma-xi-
mum r ange d
escent speed. fuel consum ed, di stance
eov ered . and eia l)Sed time from any desir ed altitude
to
sea le vel are pr esente d as a function of gr oss
weight and drag index, All data is based on an ICA O
st andard atmospher e,
The method of
presenting data for fuel, distance, and
time is identical. Theref o re, only one sample pr ob-
lem Is shown.
SAMPLE PROBLEM
Desc en t Fu el
(For figure 11- 41)
(A) I nitial gross weight . 14.0 001b
(B) Cruise altitude 35, 000 ft
(C) Dr ag index ... . .. . .. , . , .. , .
o
SAMPLE DESCENT FUEL
Not e
Section XI
P art 7
FAl-ll6
(0) Fuel required from cruise
altitude to sea level , .. , . , , ..... 112 Ib
Fr om figure 11-42, descent speed is 200
KCAS.