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As the air is pushed downwards over the wing, it results in an equal and opposite force directed upwards known as
lift.
The main purpose of the drain hole in a pitot system is
to
allow
water
to
escape.
A
complete blockage
in the pitot system will result in a higher than actual read during a climb.
A fowler flap works by
extending
rearward
,
increasing
the
area
of the
wing
causing
lift
to
increase.
Wings
spars
run from Wing root to wingtip and can be supported externally.
Semi-monocoque fuselage is a series of
round
or
oval forms
held together by
stringers
covered by an
outer skin
which bears
part
of the load.
The primary purpose of the the nose skid on a glider is to protect the
fuselage
under-surface
from
damage.
Fuselage of the 2-33 is a
truss-type welded steel tube.
Gliders most often utilize
Central Main wheel
with small
outrigger
wingtip wheels or skids as landing gear configuration.
Ailerons
,
Roll Spoiler
create movement about the longitudinal axis.
Trim device
is used to reduce fatigue on the pilot, allow more precise flying and to reduce pilot workload.
Dive breaks on an aircraft are used to increase
profile
drag.
The three axes on aircraft are
lateral longitudinal
and
vertical.
All the aircraft axes pass through the
center
of
gravity.
Mass balance
is designed to prevent
control
surface
flutter.
Wingspan of a Schweizer 2-33 is
51’.
aero-tow hook location on a 2-33 is located on the
centerline
of the aircraft approximately
2
ft aft the
underside
of the nose.
Calibrated airspeed
(
CAS
) is indicated airspeed corrected for
position
and
instrument error.
Equivalent airspeed
(
EAS
) is calibrated airspeed corrected for compressibility error.
Indicated airspeed
(
IAS
) is the uncorrected airspeed read from the airspeed indicator face.
True AirSpeed
(
TAS
) is Calibrated airspeed corrected for density.
The objective of “swinging” a compass is to
minimize
error
and
record
the
deviation
on
various
headings.
Turning to the South will cause a compass to
lag
; turning towards the North will cause the compass to
lead.
A gyro when spinning has the tendency to remain spinning in that plane of motion, this is known as
rigidity
in
space.
V’s are the marking on the ASI found at the
bottom
of the green arc and tells the pilot the
stall speeds
in the cruise configuration.
Deviation is the error caused by
magnetic components.
Temperature error, position error, mountain effect are all instrument errors with the
altimeter.
The load factor of an aircraft at a
45°
of bank is
1.41g’s.
The critical angle for most
conventional
airfoils is
17°.
A bank greater than 60° would constitute an
automatic
maneuver.
When a light category aircraft is following a medium category aircraft the minimum distance to avoid wake turbulence is
4nm.
The total lift force acting on an aerofoil in flight is considered to act at
90°
to the
average relative air flow.
Load factors are expressed as
G-Force.
Propellers
create
forward thrust
by
accelerating
a
massive air reward.
Yaw
and
roll
are interlinked.
Movement about the lateral axis is called
pitch.
The most important factor for directional stability is the
vertical stabilizer.
The most important factor for pitch stability is the
position
of the
center
of
gravity.
Directional stability is stability in
yaw.
Auto rotation occurs by
yaw
altering the
airflow
over each wing resulting in one wing becoming more
stalled.
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