Douglas A-4M - PART 3 CLIMB; CLIMB

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NAVATH.

01- 40AVl\.'1- 1

Section

Xl

Part

3

PART

3

CLIMB

CLIMB

Climb

charts

(figu

res

11-16

through

11

-20)

present

the

climb

performance

for

all

drag

index

configura-

tio

ns

with

the

engine

operating

<It

military

thrust.

Climb

sp

eeds

are

presented

in

figure

11

-16

as

a

func-

tion

of

drag

index

but

independent

of

gross

weight.

The

climb

speed

schedu

le

is

based

on a

minimum

time

to

climb

and

does

not

represent

;1

maximum

range

climb.

Fuel.

distance.

and

lime

to

climb

arc

presented

in

figures

11-17

through

J 1

-19

as

a

function

of

gr

oss

weight.

pressure

altitude.

drag

index

.

and

tempera-

tu

re

deviation

from

leAO

s

tandard

day.

The

d.1.1a

are

based

on

the

climb

speed

schedule

show

n in

fi

g-

ure

11-16.

SAMPLE

PROBLEM

Climb

Spe

ed Schedule

(For

figure

1

1-16

)

(A)

Cruise

altitude

(B)

Drag

index

(C)

Climb

speed

at

cruise

altitude

(D)

Initial

climb

altitude

(E)

Climb

speed

at

initial

a

Jtitude.

SAMPLE

PROBLEM

Climb

Fue

l

30,000

fl

50

292 KCAS

5000

ft

3

45

KCAS

The

method

of pr

es

en

ti

ng

da

ta

for

fuel.

distance.

and

time

is

identical;

therefore,

onLy

one

sample

is

shown.

(For

figure

11-17)

SAMPLE

CLIMB

SP

EED

SCHEDULE

(A) In

itial

gross

wei

ght

(B)

Cruise

a

ltitude

(e)

Dr

ag

index

..

.

(D)

Temperature

baseline

(E)

Temp

er atu

re

deviation

from

ICAO

standard

day.

(F)

Fuel

to

climb

from

sea

le

veL

.....

.

FA1

·1l8

18.000

Lb

30

.000

it

50

525 lb

COMBAT CEILING

AND

OPTIMUM

CRUISE

ALTITUDE

C

om

bat

ceiling,

th

e

al

titude

for

500-fpm

rate

of

climb

with

military

thru

st,

and opti

mum

c

ruis

e

11

-

31