Block Xiv - Fundamentals Of Flight

Front 1

A. The Physics of Flight (Ref a)

Back 1

Motion is the act, or process, of changing place or position; simply put, motion is movement.

Front 2

Motion is the basic fundamental of aviation, the 3 types of motion pertaining to flight are:
Acceleration

Back 2

The rate of change of the speed and or velocity of matter
with time.

Front 3

Speed.

Back 3

The rate of movement in terms of distance measured in an allotted amount of time

Front 4

Velocity.

Back 4

The quickness or speed of an object in a given time and
direction.

Front 5

Laws of motion:
Newton's First Law.

Back 5

According to Newton's first law of motion (inertia), an
object at rest will remain at rest, or an object in motion will continue in
motion at the same speed and in the same direction, until acted upon by an outside force.

Front 6

Newton's Second Law.

Back 6

The second law of motion (force) states that if an objec
moving with uniform speed is acted upon by an external force, the change of
motion, or acceleration, will be directly proportional to the amount of force and
inversely proportional to the mass of the object being moved.

Front 7

Newton's Third Law.

Back 7

The third law of motion (action and reaction) states that
for every action there is an equal and opposite reaction.

Front 8

Bernoulli's principle.

Back 8

The principle states that when a fluid flowing through
a tube reaches a constriction or narrowing of the tube, the speed of the fluid
passing through the constriction is increased and its pressure decreased. The
general lift of an airfoil is dependent upon the airfoil's ability to create circulation in the air stream and develop the lifting pressure over the airfoil
surface. As the relative wind strikes the leading edge of the airfoil, the flow of air is split. Part of the air is deflected upward and aft, and the rest is
deflected down and aft. Since the upper surface of the wing has camber, or a curve, the flow over its surface is disrupted, and this causes a wavelike effect to the wing. The lower surface is relatively flat. Lift is accomplished by the
difference in the airflow across the airfoil

Front 9

B. Principles of Flight and Aeronautic Terms (Ref a)
Lift.

Back 9

the air. equal to The force that acts, in an upward direction, to support the aircraft in It counteracts the effects of weight. Lift must be greater than orweight if flight is to be sustained.

Front 10

Weight.

Back 10

The force of gravity acting downward on the aircraft and everything on the aircraft.

Front 11

Drag.

Back 11

The force that tends to hold an aircraft back. Drag is caused by the disruption of the air about the wings, fuselage or body, and all protruding objects on the aircraft. Drag resists motion.

Front 12

Thrust.

Back 12

The force developed by the aircraft's engine, and it acts in the forward direction. Thrust must be greater than or equal to the effects of drag in order for flight to begin or be sustained.

Front 13

Aircraft axis:
Longitudinal axis.

Back 13

An imaginary reference line running down the center of
the aircraft between the nose and tail.

Front 14

Lateral axis.

Back 14

An imaginary reference line running parallel to the wings

Front 15

Vertical axis.

Back 15

An imaginary reference line running from the top to the
bottom of the aircraft.

Front 16

B. Basic Aircraft Components and Equipment (Ref a)
Aircraft have movable surfaces installed that cause and control movement or
rotation about the three axis.
Fixed wing aircraft:
Ailerons (roll).

Back 16

longitudinal axis.

Front 17

Elevators (pitch).

Back 17

lateral axis.

Front 18

Rudder (yaw).

Back 18

vertical axis.

Front 19

Rotary wing aircraft:
The cyclic stick (roll/pitch

Back 19

Tilts the plane (angle) of the rotor blades forward, aft or sideways, giving the helicopter its directional motion by changing the direction of the lift; from vertical to a varying degree based on a 0° centerline.

Front 20

Tail rotor (yaw).

Back 20

This component counteracts torque of the main rotor by
increasing or decreasing the amount of horizontal thrust the tail rotor produces, this movement is around the vertical axis.

Front 21

The following is a list of non axis affecting flight controls; they mayor may not be installed on all aircraft.
Flap (leading/trailing edge)

Back 21

section of the wing resulting
landing rollout.Creates extra lift by lengthening the top
in maximum lift to reduce takeoff runs and

Front 22

Spoiler.

Back 22

Used to decrease or spoil wing lift by destroying the smooth flow of air over the wing surfaces, this creates a more predictable landing glideslope.

Front 23

Speed brakes

Back 23

Hinged or moveable control surfaces used for reducing the
speed of aircraft. Location varies on the model of aircraft; however the purpose remains the same

Front 24

Slats.

Back 24

Slats are movable control surfaces attached to the leading edge of the wing. When open, or extended forward, a slot is created between the
slat and the wing leading edge. High-energy air is introduced into the
boundary layer over the top of the wing. At low airspeeds, this improves the lateral control handling characteristics, allowing the aircraft to be controlled at airspeeds below the normal landing speed. This is known as boundary layer control.

Front 25

Unique flight terms and conditions: Collective

Back 25

The main rotor of a helicopter consists of two or more rotor
blades. Lift is accomplished by rotating the blades through the air at a high rate of speed. Lift may be changed by collectively increasing the angle of attack or pitch of the rotor blades. When the rotor is turning and the blades
are at zero angle (flat pitch), no lift is developed.

Front 26

Angle of Attack (AoA).

Back 26

The angle at which the airfoil or fuselage meets a flow
of air. Defined as the angle between the chord line of the wing (an imaginary
straight line from the leading edge to the trailing edge of the wing) and the relative wind. The relative wind is the direction of the air stream in relationship to the wing. Angle of attack is measured in "units" as opposed to degrees.

Front 27

Autorotation

Back 27

A method of allowing a helicopter to land safely from altitude without using engine power. As a helicopter is descending in altitude the
collective is lowered allowing the reverse airflow through the rotor to maintain
RPM. When the helicopter reaches a predetermined altitude the collective pitch
is increased to convert inertial energy into lift to reduce the rate of descent and cushion the landing.

Front 28

Basic aircraft hydraulic system: A reservoir

Back 28

to hold a supply of hydraulic fluid.

Front 29

A pump to

Back 29

provide a flow of fluid.

Front 30

Tubing

Back 30

to transmit the fluid.

Front 31

A selector valve

Back 31

to direct the flow of fluid.

Front 32

An actuating unit to convert

Back 32

the fluid pressure into useful work

Front 33

Landing gear main components and their purpose:
Shock Strut Assembly

Back 33

Absorbs the shock that otherwise would be sustained
by the airframe.

Front 34

Tires

Back 34

Allows the aircraft to roll easily and provides traction during takeoff and landing.

Front 35

Wheel Brake Assembly

Back 35

Used to slow and stop the aircraft. Also used to prevent the aircraft from rolling while parked.

Front 36

Retracting and Extending Mechanism

Back 36

All the necessary hardware to
electrically or hydraulically extend and retract the landing gear

Front 37

Side Struts and Supports

Back 37

Provides lateral strength/support for the landing
gear.
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