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ropellers
1ZI
22)
Question 314 in database)
On take off the directional control of a nose-wheel aircraft will be affected by:
a) gyroscopic and asymmetric blade effect.
Question 369 in database)
The angle of attack of a fixed pitch prop:
a) is lower in the t8 Re off run than in flight.
b) is optimum in t l i Q . 9 ~ : G - _ - : 1 GS
c) is optimum in stabilised cruise flight.
d) decreases with decrease in speed at constant engine RPM.
The correct answer is c
Question 58 in database)
Which of the following will increase the angle of attack of a fixed pitch propeller blade?
a) Increased TAS and increased RPM.
Question 368 in database)
The advantage of a constant speed propeller over a fixed pitch propeller is:
a) higher maximu available.
b) higher maximum etrlCiency
G-1
GS
c) more blade suiface area available.
d
nearly maximum efficiency over wide speed range.
The correct answer is d
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Question 53 (in database)
A propeller blade
is
twisted along its length
in
order
10
:
a) give a progressively increasing blade angle from
roollo
tip.
b) give a progressively increasing pitch from root 10 tip.
c) m p n s t
decreasing linear speed of the blade
,
d) maintain the optima
An
gle of-Atta
The correct answer is d.
1 ;-1
Question 55 (in database)
As an aircraft with a variable-pitch, constanl-speed propeller accelerates along the runway:
a)
th
e angle of at
t CJ<
will decrease and the engine RPM remain constant
b) the blade pitch a ~ e i n c r e a
r
i ~ . r i n g a constant angle of attack
and
RPM.
c) Ihe angle of altack will remain constant and the engine RPM will increase.
d)
th
e linear velocity of the propeller tip will gradually decrease.
The correct answer is b.
Question
308 in
database)
If
an
aircraft with a fixed pitch propeller reduces speed the engine RPM will also reduce if the
throttle
is
not moved; this
is
because:
a) the increase
in
blade angle of attack increases propeller torque, thereby imposing a greater
load on the engine.
b d , d 1 0 ' th
,;,
;otak, d 009;06 pow ,
c) the windmill effect is lessen
l1
= l
GS
d) the angle of attack of the propeller blades has decreased.
The correct answer is a. •
Question
361 in
database)
Propeller blade angle of attack is the angle between the chord and the:
a) direction of axis of the propeller.
b) aeroplane heading.
c) relative
,;0,0;
.
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Question 315 (in database)
On take off the directional control of a tail-wheel aircraft will be affected :
a) gyroscopic
an
lf a symmetric blade effect.
"
b) slipstream and tor :lue effect
G
_
1
GS
c) all the phenomena at Opt ions a) and b).
d none of the phenomena at Options a) and b).
The correct answer is c.
Question 362 (in database)
What is the purpose of increasing the number of propeller blades?
a) To reduce noise.
b) To improve absorption.
c) To increase
f f i c i e n c y
of
the variable pitch mechanism.
i.
d To enable a Ion
e u n d e r r
t t e d .
The correct answer IS b.
lJ
Question 364 (in database)
During the take off roll , what affect does torque have on an aircraft with a clockwise rotating
propeller?
a) Weight on
l e l f
decreased, weight on right wheel incra sed.
,
b) Weight on left whee I n c r e a s ~ ~ right wheel remains constant.
c) Weight on left wheel increased, weight on right wheel decreased.
d Weight on right wheel increased, weight on left whee decreased.
The correct answer is c.
Question 306 (in database)
On the take off roll a nose-wheel aircraft has less tendency to swing than a tail-wheel aircraft
because:
a) the pilot has a better view.
b) the effect of" ~ l I e r torque is cancelled out y the slipstream effect.
c) it does not su ff
er
fr
Of l gyroscopic and aSY fnetric blade effect.
d the propeller normally
r o t a t
~ n
~ ~ ~ s i t e
direction.
The correct answer is c.
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Question 365
(in
database)
Which of the following definitions of propeller parameters
is
correct?
a)
Blade Angle
is
the angle between chord line and propeller axis.
b)
Critical tip e propeller speed at which ..there
is
a risk of the flow separating at some
part of the propeller.
. 'i._
..
~
c) Blade angle of attack
is
the Mgr
J
~ chord line and propeller vertical axis
d) Geometric propeller pitch
is
the theoretical dis
tan ce
nvelled forwa
rd y
the propeller
in
one
rotation.
The correct answer
is
d.
Question 360 (in database)
T
he
angle of attack of a fixed pitch propeller designed for cruising flight, measured at
its
reference station,
is
:
a) optim
um in
steady cruising flight only.
b) increases
c r e s e
in
TAS.
c) decreases
w
c r e s e in
RPM.
d will always be positive
in
a
rf6;;e
T q ~
The correct answer
is
a.
Question
57
(in database)
In a single·engine, propeller-driven aircraft, the torque reaction of a clockv.ise rotating propeller
(as seen from the pilot s seat) will tend to cause:
a) left roll
and
~ w during
take
off.
,
,
b)
left roll
and
left uring
A G S
c) right roll and right yaw during take off.
d) left y w and right mll during
take
o
ff
.
T
he
correct answer
is b.
Question 309 (in database)
A fixed pitch propeller with a coarse blade angle would ensure
an
economic relatively high
cruising speed. Why are such propellers not fitted to the average light aircraft?
a) Because the reduction
in
take o
ff
performance would not be acceptable.
b) Because it too noisy.
c) Because fuel
c:
Dptio .
the
climb
an
d the descent-wo
ul
d
6e
uneconomical.
d None of the above.
The correct answer
is
a.
G-1AGS
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Question 54 (in database)
Blade angle from the hub to the tip of a propeller blade in order to maintain an
optimal rom hub to tip.
a) increases
,
b) decreases
eometric l GS
c) increases effective Pitch
d) decreases angle of Attack
The correct answer is d.
Question 366 (in database)
Why does the blade angle of a propeller decrease from root to tip?
a) To compensate for the change in geometric cross section.
b) To provide increased thrust at root.
c) Cross-sectionalSegment increases from tip to root.
.
,
d) To compensate
for
the increased{v
A'ff
ty
of
the blade tip.
T
he
correct answer is d. I :J
-
Question 363 (in database)
What would
be
the gyroscopic effect of a clockwise rotating propeller (viewed from the pilot s
seat) on a single-engine, tail-wheel aircraft
as
it raises
its
tail during the take off run?
,
b) The aircraft would yaw to GS
c) The aircraft would roll to the right.
d) The aircraft would roll to the left.
The correct answer
is b
Question 359 (in database)
A propeller blade
is
twisted from root to tip:
a) to provide maximum thrust at the root.
b) to
provide maximum thrust at the tip.
c) because the
J l g l e
of attack of the segment
is
dependent on segment movement
in
the
plane of rotation and the aircra true air speed.
d) because the local angle of
l ~ W S s g m
t
Is
dependent on segment movement in the
plane of rotation and the segment velocity.
The correct answer
is
d.
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