Download Aero 1 Flashcards

Define:
Scalar Quantity, Vector Quantity
Force, Mass
Volume, Density
Weight, Moment
Power, Energy
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Potential Energy
Kinetic Entergy
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Scalar Quantity: quantity that represents only magnitude ie
time or temp
Vector Quantity: quantity that represents magnitude and
distance ie F, a
Force: m * a, it is a push pull exerted on a body
Mass: m, the quantity of molecular material that compromises
an object
Volume: v, the amount of space occupied by an object
Density: , mass per unit volume
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Weight: the force with which a mass is attracted to the earth’s
center
Moment: a vector quantity equal to a force times a distance
from the point of rotation that is perpendicular to the force
Power: rate of doing work or work done per unit time (scalar
quantity)
Energy: scalar measure of a body’s capacity to do work
Potential Energy: PE=mgh, ability to do work because of its
position or state of being
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Kinetic Entergy: KE=1/2mV2
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State Newton’s Three Laws of Motion
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1) Law of Equilibrium- A body at rest tends to
stay at rest and a body in motion tends to
remain in motion in a straight line at a
constant velocity unless acted upon by some
unbalanced force
2) Law of Acceleration: An unbalanced force
acting on a body produces an acceleration in
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the direction of the force that is directly
proportional to the force and inversely
proportional to the mass of the body
3) The Law of Interaction: For every action, there
is an equal and opposite reaction
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Examples of the Law’s of Motion
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1) an airplane in equilibrium flight with no
change in acceleration that is level and
in constant velocity
2) increasing the throttle on a plane
produces more thrust than drag causing
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the airplane to accelerate till they are
equal
3) if a jet fires hot gases rearward, it will
move forward
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Define, Compare and Contrast
Equilibrium and Trimmed Flight
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Equilibrium is the absence of acceleration
either linear r angular. It exist when the
sum of all the forces and the sum of the
moment around the COG are equal to zero
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Trimmed exist when the sum of the
moments around the COG is zero.
In trimmed flight, the sum of the forces
may not be equal to zero since you can
trim a airplane into a turn.
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Define:
Static Pressure, Air Density
Temperature, Lapse Rate
Humidity, Viscosity
Local Speed of Sound
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Include any important relationships
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Static Pressure: pressure each air particle exerts on another.
Atmospheric static pressure decreases with altitude increase
Air Density: , the total mass of air particle per unit of volume.
Air Density decreases with altitude increase
Temperature: the average kinetic energy of the air particles.
Lapse Rate: the linear decrease in air temperature as you
increase altitude at 2oC/1000’ or 3.57oF/1000’. Decreases till
36,000’
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Humidity: the amount of water vapor in the air. As humidity
increases, air density decreases
Viscosity: a measure of the air’s resistance to flow or shearing
(stickiness). Air viscosity increases with an increase in
temperature
Local Speed of Sound: the rate at which sound waves travel
through an air mass. As temperature increases, LSOS
increases. Sound is a wave motion... not particle!
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State the pressure, temperature, lapse rate
At sea level using Metric and English units
for
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A standard atmosphere
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Metric
Pressure
Temperature
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1013.2mb
15C
English
29.92 in-HG
59F
Lapse Rate
3.57F/1000’
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2C/1000’
State the relationship between altitude and
temperature,
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Pressure, air density and local speed of
sound
Within the standard atmosphere
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As you increase altitude, temperature
decreases to 36,000’ , pressure
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decreases, air density decreases, and the
local speed of sound decreases
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State the relationship between
Pressure, Temperature, and Air Density
Using the General Gas Law
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P=RT
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If pressure is held constant ie constant
altitude, then  and temperature will be
inversely proportional to eachother
Bonus Card:
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Altitude is defined as the height above a given plane of
reference.
True Altitude is the actual height above mean sea level
Pressure Altitude is the height above the standard data plane
Density Altitude is the altitude in the standard atmosphere
where the air density is equal to the local air density and if
found by correcting pressure altitude for temperature
deviations from standard atmosphere.
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A high DA indicates a low air density and will decrease
aircraft’s performance because the power being produced by
the engines is getting fewer molecules to burn
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Define, Compare Contrast
an Aircraft and an Airplane
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An aircraft is any device used or intended to be
used for flight in the air. It is either supported by
buoyancy of the structure or by dynamic reaction
of the air against its surfaces
An airplane is a heavier than air, fixed wing
aircraft that is driven by an engine (propeller or
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jet) and is supported by the dynamic reaction of
the air against its wings.
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T-34:
Unpressurized, low winged monoplane, tricycle
landing gear, single engine turboprop, tandem
cockpit, semi-monocoque fuselage, slotted flaps,
33’5” wingspan, tapered wings, dihedral wings,
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List and Describe the
Three major control surfaces of an
Airplane
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Ailerons – are attached to the wing to control roll
Elevators – are the horizontal surface attached to
the horizontal stabilizer to control pitch
Rudder – is the upright surface attached to the
vertical stabilizer to control yaw
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List and describe the five major
Components of an airplane
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Fuselage: basic structure of the airplane to which
all the other components are attached
Empennage: assembly of stabilizing and control
surfaces on the tail of an airplane
Wing: airfoil attached to the fuselage and is
designed to produce lift
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Landing Gear: permits ground taxi and absorbs
the landings shock
Engine: provide the thrust necessary for powered
flight
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List and define the components
of an airplane referencing system
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Consist of three mutually perpendicular lines intersection at a
point called the center of gravity. This point is where all the
weight is concentrated and where all the forces and moments
are measured
Longitudinal Axis: passes from nose to tail, movement of the
lateral around this is called roll and controlled by the ailerons
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Lateral Axis: passes from wingtip to wingtip, movement of
longitudinal axis around this axis is called pitch and controlled
by the elevators
Vertical Axis: passes vertically thru the COG, movement of the
longitudinal axis about the vertical axis is directional control
and produces yaw from the rudders
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Define:
Wingspan, Chordline, Chord
Tip/Root Chord, Average Chord
Wing Area, Taper, Taper Ratio, Sweep
Angle
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Aspect Ratio, Wing Loading
Angle of Incidence, Dihedral Angle
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Wingspan: b, the length of the wing from tip to tip
Chordline: an infinitely long line from the leading to the trailing edges
of an airfoil
Chord: a measure of the width of the wing or control surface
Tip/Root Chord: measure of the chord at wing tip and wing root
Average Chord: c, is the average of every chord from wing root to
wing tip
Wing Area: S=b*c, the apparent surface area of a wing from wingtip
to wingtip
Taper: the reduction in the chord of an airfoil from root to tip
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Taper Ratio: =Chord tip/root, ratio of tip chord to root chord
Sweep Angle: , is the angle between a line drawn 25% aft of the
leading edge and parralle to the lateral axis
Aspect Ratio: AR=b/c, the ratio of the wingspan to the average chord
Wing Loading: WL=weight/wing area, ratio of the planes weight to
the surface area
Angle of Incidence: angle between the plane’s longitudinal axis and
the chordline
Dihedral Angle the angel between the spanwise inclination of the
wing and the lateral axis
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State the advantages of
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Semi-monocoque fuselage construction
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Semi-monocoque fuselages have skin,
transverse frame members, and stringers which
all share in the stress load and are easily
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repaired if damaged. It is the happy medium
between a truss and a full-monocoque.
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Describe a Full Cantilever
Wing Construction
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A wing with all internal bracing
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Define:
Steady Airflow, Streamlines, and
Streamtube
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Steady Airflow: exist if at every point in the
airflow there is a steady static pressure, density,
temperature and velocity
Streamlines: the path that air particles follow in
steady airflow
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Streamtube: a collection of streamlines form a
tube which contains flow that is effectively
equivalent to a tube
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Describe the relationship between airflow
velocity
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and cross sectional area within a stream
tube
using the continuity equation
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A1V1 = A2V2
If under supersonic airflow, density is eliminated.
The massflow in must equal the massflow out. If
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A2 decreases, then V2 must increase. This
makes area and velocity inversely related.
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Describe the relationship between total
pressure, static pressure, and dynamic
pressure using Bernoulli’s Equation
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Total Pressure = Static Pressure + Dynamic
Pressure
Total Pressure must remain constant within a
closed system. As area in a streamline
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decreases, velocity increases, dynamic pressure
increases and forces static pressure to decrease.
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List the components of a
Pitot-Static System
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Pitot Tube, Black Box, Static Pressure Port
This device collects Total Pressure (Pitot Tube),
and ambient Static Pressure (Static Pressure
Port)
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Q=Pt-Ps (Black Box converts Q into a IAS
velocity)
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Define:
Indicate Air Speed, Calibrated AS
Equivalent AS, True AS
Ground Speed
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Indicate Air Speed: instrument indication for the dynamic
pressure the airplane creates during flight
Calibrated AS: taking the IAS and calibrating for instrumental
error (caused by the static pressure port accumulating
erroneous static pressure from slip stream flow)
Equivalent AS: takes the CAS and corrects for compressibility
caused by the ram effect of air at high speeds. It is the true
AS at sea level on a standard day that produces the same q
as the actual flight conditions
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True AS: the actual velocity at which the plane moves thru an
airmass found by correcting EAS for density. TAS will equal
IAS only under standard day and sea level conditions!
Ground Speed: is a measure of the planes actual speed over
the ground. TAS is thru an airmass and GS is corrected for
wind
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Describe the relationship of IAS, TAS, GS
and Altitude
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Air density decreases when you increase
temperature and altitude, if IAS remains constant
while climbing from sea level to some higher
altitude, TAS must increase. TAS will be about 3
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knots faster than IAS for every thousand feet of
altitude.
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Describe the effects of wind on IAS, TAS,
and GS
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GS is found by correcting the TAS for the
movement of the air mass. GS = TAS –
Headwind or + a Tailwind
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Define:
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Mach Number: M = TAS / LSOS, it is the ratio of
the airplane’s TAS to the local speed of sound
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Critical Mach Number: the free air stream mach
number that produces the first evidence of local
sonic flow
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Define Pitch Attitude, Flight Path, Relative
Wind, Angle of Attack, Mean Camber Line,
Positive Camber Line, Negative Camber
Line, Symmetric Camber Line,
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Aerodynamic Center, Airfoil Thickness,
Spanwise Flow, Chordwise Flow
Pitch Attitude: , angle between a plane’s longitudinal axis and the
horizon
Flight Path: the path described by a plane’s COG as it moves thru an
airmass
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Relative Wind: the airflow the plane experiences as it moves thru the
air. It is equal in magnitude and opposite in direction of the flight
path
Angle of Attack: , angle between the relative wind and the chorline
of the airfoil
Mean Camber Line: line drawn halfway between the upper and lower
surfaces of a wing
Positive/Negative/Symmetric Camber Line: description of the above
line
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Aerodynamic Center: is the quarter chord point of the chordline and
remains constant until supersonic flight is reached (23 – 27%)
Airfoil Thickness: The point of maximum thickness corresponding to
the aerodynamic center
Spanwise Flow: Air flow that travels along the span of the wing and
produces no lift
Chordwise Flow: Air flow that travels at rigth angles to the leading
edge and accelerates over the wing causing lift!
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Define:
Aerodynamic Force, Lift
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Drag
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Aerodynamic
Force: is a force that is the result of
pressure and friction distribution over an airfoil and can
be described by lift and drag
Lift: the component of the aerodynamic force acting
perpendicular to the relative wind
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Drag: the component of the aerodynamic force acting
parallel to and in the same direction as the relative wind
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Describe the effects on dynamic pressure,
static pressure, and the aerodynamic force
as air flows around a cambered airfoil and
symmetric airfoil
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As air flows over the top of a wing, it must travel
farther and at a higher velocity. The static
pressure above the wing is less than the
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pressure below creating in upward pull and a
lifting force.
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Describe the effects of density, velocity,
surface area, camber, and angle of attack
on lift
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An increase in density or velocity or a wing’s
surface area produces greater lift
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