Douglas A-4M - Page 21

Section XI NA VAIR 01-4 0AVM · l
Part3
SAMPLE CLIM B FUEl SAMPLE Ca.\BAT CEILING AND OPTIMUM
.... 1-119
altitude, the altitude that will produce the maJdmum
cruise distance per pound of fuel, a re presented in
figure
11-20. The d,t., ar e presented as a function
of gross weight and drag Index.
SAMPLE PROBLEM
Combat Ceiling and Optimum Cru ise Altitude
(For figure 11-20)
11-32
CRUISE ALT I TUDE
CO I,j a..,T CEIUNG
OPTIMUM CRUISE ALTITl(lE
FAl-)20
(A) Aircraft gross weight. . . . . . . . . .. 18,000 lb
( B) Drag index ..........•.
.. 50
(C) Combat ceiling ....
40,400 ft
(D) Optimum cruise altitude .. .
. •• 34,OOQ ft