Douglas A-4M - PART 9 COMBAT PERFORMANCE; TURNING RADIUS; MANEUVERABILITY

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NAVAlR

0

1-4

0AVl\1-J

Section

Xl

Part

9

PART

9

COMBAT

PERFORMANCE

COMBAT

PERFORMANCE

This

part

contains

the

performance

ch

aTt

s

associated

with

the

combat

phase

of

the

mission

.

Turnin

g

radius,

maneuverability,

maximulll Mach num':ler.

and

military

fuel flow

are

included.

TURNING

RADIUS

The

turning

radius

nomograph,

fib'Ul"e

11-47,

pre-

Se

nts

d,1t3

for

steady state

Jeveltut'ns

as a fUnctiOn

of

true

airspccd,

normal

load

factor,

bank

angle,

distance

traveled.

and

heading

change

. When

used

in

conjunction

with

the

load

factor

limitations

of

the

maneuverabillty

charts,

figure

11-4

8,

the

aerodyn-

:rnic

,

enginc.

and

structural

characteristics

of

the

aircraft

arc

takcn

into

a

ccou

nt.

Note

At

norlllal low

level

airspeeds

a

rough

plan-

ning :lid

for

turning

radius

is

the

use

of

a

dime

on

an

ONe

(l

:1, 000, 000)

or

a

quarter

on

a PC

(J

:500, 000).

SAM

PLE

PROBLEM

Turning Radius

(For

rtgurc

11-47)

From

ManeU\'erabUity

Sample

Pr

oblem

ure

J

1-48)

Mach

Number

Normal

Load

Factor

...

(A)

Normal

Load

Factor

.....

.

(J3ank

Angle.

.

74.6

Degrees)

I

(Fig-

O.

75

3.84g

3.84g

SAMPLE

TURNING RADIUS

®

--

---

..........

©

---

--

TRUE

111&11

toan

un

IIUmO

tUIU5

fACTOR

mLE

--

---_ill

---

-

-

,

IURI

ISIlN E

",.,

•

UGIUS

lunun

1M

•

U~"

CII'N~E

fA-I-DO

(8)

True

Airspeed

(C) Turning

Radius

496 KTAS

6OQOft

(0)

H

eading

change

90

deJtrees

(E)

Distancc

Travcled

in

Turn

9200 rt

MANEUVERABILITY

Low-altitude

maneuverab

ilit

y

characteristics

of

the

A-4M

aircraft

are

shown

in

figure

11-48.

These

data

provide

a

means

of

determining

either

the

maximum

load

fador

attainable

at

a

speCified

Mach

number

(sample

problem

1)

or

the

maximum

(and

minimum)

Mach

number

for

a

predetermined

load

factor

re-

quirement

(sample

problem

2).

These

data

are

pre-

sented:ts

a function of

altitude,

normal

load

factol'

11-93