AERT 4040 Flashcards
Aerodynamics
Density Altitude is used as a predictor of aircraft performance, not as a height reference.
True
False
True
An aircraft’s Mach Number is the aircraft’s
Local Speed of Sound divided by TAS
IAS divided by the Local Speed of Sound
TAS divided by the Local Speed of Sound
TAS divided by the Local Speed of Sound
The temperature and pressure conditions for a standard day are ______________.
59 degrees F / 15 degrees C and 29.92 in of Hg / 1013 mbar
There is no such thing as a standard day
68 degrees F / 20 degrees C and 30.30 in of Hg / 1026 mbar
59 degrees F / 15 degrees C and 29.92 in of Hg / 1013 mbar
What did the Wright brothers think was the most difficult problem, thus the first problem they attacked when building their Flyer?
Design of the wings
How to control and balance the aircraft
Developing a means of propulsion
How to control and balance the aircraft
Density is
is always expressed by Liters per Pound
Mass per unit volume
Weight per unit volume
Mass per unit volume
The Critical Mach Number of an aircraft is the highest Mach Number the aircraft can travel before structural damage is done to the airframe.
True
False
False
How did the Wrights correct their problem of roll reversal?
They used a canard rather than an elevator
They used counter-rotations propellers
They developed a movable rudder and connected it to the roll control
They developed a movable rudder and connected it to the roll control
What method did the Wright brothers use to control roll?
The used what was later called flight spoilers
They developed a technique of wing warping
They developed ailerons
They developed a technique of wing warping
The speed of sound in air is dependent upon the
Air Density only
A combination of Air Temperature, Air Density and Humidity
Air Temperature only
Air Temperature only
What was unique about the engine that the Wrights used for their Flyer?
It was the first time aluminum was used in the construction od an aircraft
It was the first use of 100 LL fuel
It was the first use of a six cylinder engine
It was the first time aluminum was used in the construction od an aircraft
Air viscosity __________ as the air temperature increases.
Increases
Stays the same
Decreases
increases
Total pressure is:
measured parallel to the local stream
1/2ρV²
static pressure minus dynamic pressure
static pressure plus dynamic pressure
static pressure plus dynamic pressure
The General Gas Law sets the relationship between three properties of air: pressure (P), density (ρ), and temperature (T). It is expressed as an equation where R is a constant for any given gas. What is the correct expression of the General Gas Law.
ρT = PR
ρP = RT
ρ = P/RT
ρPT =
ρ = P/RT
The Law of Interaction states __________.
“Two opposite forces cannot interact.”
“An unbalanced force acting upon a body produces an acceleration in the direction of the force that is directly proportional to the force and inversely proportional to the mass of the body.”
“A body at rest tends to stay at rest.”
“For every action there is an equal and opposite reaction.”
“For every action there is an equal and opposite reaction.”
The angle of incidence of a wing is the angle between a line drawn through the 25% cord points and a line drawn parallel to the lateral axis.
True
Fasle
False
Static pressure acts:
in the direction of the flow
perpendicular to the surface that any air molecules collide with.
perpendicular to the direction of flow
in the direction of the total pressure
perpendicular to the surface that any air molecules collide with.
A moment is _________.
created when a force is applied at some distance from an axis or fulcrum, producing rotation about that point
the result of mass x acceleration
a body’s capacity to do work
the force with which a mass is attracted toward the center of the earth
created when a force is applied at some distance from an axis or fulcrum, producing rotation about that point
The center of gravity is the point at which __________.
lift is generated
all weight is concentrated
all aerodynamic forces are concentrated
elevator authority is lost
all weight is concentrated
Wing Loading is:
the aircraft weight divided by the sine of the wing dihedral
the ratio of the aircraft weight to the surface area of the wing
the ratio of the aircraft weight to the wing span
the ratio of the aircraft weight to the volume of the wing
the ratio of the aircraft weight to the surface area of the wing
The Mean Camber Line:
is a line drawn halfway between the wing root and the wing tip/
is the line drawn perpendicular to the aerodynamic center of the wing
is a line drawn halfway between the leading edge and trailing edge of the wing
is a line drawn halfway between the upper and lower surface of an airfoil.
is a line drawn halfway between the upper and lower surface of an airfoil.
The chord of an airfoil is defined as ___________.
an infinitely long line drawn through the leading and trailing edges of an airfoil
a measure of the wing along the chord line, from the leading edge to the trailing edge
the angle between the longitudinal axis and the horizon
the length of a wing
a measure of the wing along the chord line, from the leading edge to the trailing edge
Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
F = ma
a = Fm
m = Fa
F = m/a
F = ma
The angle of attack of a wing is the angle between the wing’s cord and the horizon
True
False
False
The axis is which the aircraft nose moves left or right about the center of gravity
pitch
yaw
center
roll
yaw