AERODYNAMICS EXAM #7
1) How does an increase in altitude affect static pressure?
a) Increase
b) Remains the same
c) Decreases
2) What equation expresses the General Gas Law?
a) P = pKT
b) P = p*RT
c) P = pT
d) RP = pT
3) If altitude is held constant, a decrease in temperature has what affect on density?
a) Increases
b) Remains constant
c) Decrease
4) What affect does an increase in altitude have on the speed of sound and why?
a) Increase due to a decrease in temperature
b) Decrease due to a decrease in density
c) Increase due to a decrease in pressure
d) Decrease due to a decrease in temperature
5) What is the definition of density?
a) Force per unit of area
b) Mass per unit of volume
c) Mass times gravity
d) Mass times velocity squared
6) Mass is:
a) The quantity of molecular material that comprises an object
b) The amount of space occupied by an object
c) The force acting on a body as it moves
d) The rate of doing work per unit of time
7) Temperature is the measure of the average potential energy of air particles.
a) True
b) False
8) The layer of air that remains at a constant -56.5 degrees Celsius is the:
a) Boundary layer
b) Isothermal layer
c) Cold layer
d) Stable layer
9) What are the three major components that comprise an epennage?
a) Vertical Stabilizer, elevator, trim tabs
b) Horizontal stabilizer, rudder, fuselage
c) Rudder, elevator, aft part of the fuselage
d) Vertical stabilizer, horizontal stabilizer, the aft part of the fuselage
10) All motion or changes in an aircraft's attitude occurs about which position?
a) Aerodynamic center (AC)
b) Center of pressure (CP)
c) Center of gravity (CG)
d) The cockpit
11) The wingspan includes the area within the fuselage area.
a) True
b) False
12) The wings of the T-34 are tapered to:
a) Increase weight, improve structural stiffness, and reduce wing tip vortices
b) Decrease weight, improve structural stiffness, and reduce wing tip vortices
c) Increase weight, remove structural stiffness, and reduce wing tip vortices
d) Increase weight, improve structural stiffness, and increase wing tip vortices
13) Aspect ration is:
a) The ratio of the wingspan to the tip chord (CT)
b) The ratio of the root chord (CR) to the tip chord (CT)
c) The ration of the wingspan to the average chord (c)
d) The ratio of the wingspan to the root chord (CR)
14) The angle between a line drawn 25% aft of the leading edge, and a line parallel to the lateral axis is the:
a) Wing area
b) Taper angle
c) Aspect angle
d) Sweep angle
15) A negative dihedral is called:
a) Sweep angle
b) Taper angle
c) Anhedral angle
d) Spanwise angle
16) What four airflow properties must remain constant at a given point on an airfoil to have a steady airflow?
a) Viscosity, temperature, pressure, density
b) Velocity, temperature, pressure, density
c) Lift, weight, thrust, drag
d) Friction, viscosity, density, lift
17) How does the pitot-static system function?
a) It subtracts static pressure from total pressure to compute dynamic pressure
b) It subtracts pressure from dynamic pressure to compute IAS
c) It subtracts pressure from dynamic pressure to compute TAS
d) It adds/subtracts pressure and dynamic to compute total pressure
18) What type of correction must you apply to an indicated airspeed (IAS) to calculate true airspeed (TAS)?
a) Temperature correction
b) Density correction
c) Pressure correction
d) Viscosity correction
19) For steady airflow:
a) Static pressure, density, temperature, and velocity must increase
b) Static pressure, density, temperature, and velocity must remain constant
c) Static pressure, density, temperature, and velocity must decrease
20) In a steady airflow, particles dross streamlines.
a) True
b) False
21) The instrument indication for the dynamic pressure the airplane is creating during flight is:
a) Knots indicated airspeed (KIAS)
b) Indicated airspeed (IAS)
c) Airspeed
d) Calibrated airspeed
22) A pilot is flying under standard day conditions at sea level. His/her true airspeed will:
a) Equal indicated airspeed
b) Be greater than indicated airspeed
c) Be less than indicated airspeed
23) How does an increase in angle of attack affect the dynamic pressure and static pressure on the upper surface of
an airfoil?
a) The dynamic pressure decreases
b) The static pressure increases
c) The dynamic pressure increase and the static pressure remains constant
d) The dynamic pressure remains constant
24) What variables determine the amount of lift produced by an airfoil?
a) True airspeed (TAS), airfoil surface area (S), and aircraft weight (w)
b) True airspeed (TAS), airfoil surface area (S), and aircraft total drag (D T)
c) True airspeed (TAS), airfoil coefficient of lift (C L), and coefficient of total drag (DT)
d) True airspeed (TAS), air density (p), airfoil surface area (S), airfoil angle of attack, and airfoil camber
25) What must a pilot do to maintain a constant altitude and indicated airspeed as aircraft weight decreases due to
fuel consumption?
a) Maintain a constant true airspeed and reduce angle of attack
b) Increase true airspeed and reduce angle of attack
c) Increase true airspeed and increase angle of attack
d) Increase true airspeed and maintain a constant angle of attack
26) Maximum lift will be attained at what point?
a) L / D maximum AOA
b) Minimum drag AOA
c) CLMAX AOA
d) Maximum velocity airspeed
27) What is a boundary layer?
a) The airflow layer which is perpendicular to the aircraft's flight path
b) The airflow layer which demonstrates no retardation due to the airfoil's surface
c) The airflow layer which is parallel to the relative wind
d) The airflow layer which shows local airflow retardation caused by viscosity
28) In a stall what is the result of increasing AOA?
a) CL increases and lift decreases
b) CL increases and lift increases
c) CL decreases and lift increases
d) CL decreases and lift decreases
29) Using flaps _____ the stalling AOA.
a) Increases
b) Decrease
c) Does not change
30) Raising flaps from 100% to 50% reduces drag significantly without a large loss of lift.
a) True
b) False
31) As weight increases:
a) Stall speed decreases and IAS increases
b) Stall speed increases and IAS decreases
c) Stall speed increases and IAS increases
d) Stall speed decreases and IAS decreases
32) A _____ wing produces an even stall and therefore provides little warning of a stall.
a) Highly tapered wing
b) Swept wing
c) Elliptical wing
d) Moderate taper wing
33) Which of the following is correct.
a) Parasite drag is constant in level flight
b) Parasite drag equals induced drag at the 1 G stall speed
c) Induced drag is predominant at high velocities and low angles of attack
d) Parasite drag increases with the square of velocity
34) When an airfoil is at an angle of attack that produces no net lift, it is also not producing:
a) Skin friction drag
b) Form drag
c) Parasite drag
d) Induced drag
35) Minimum total drag occurs where parasite drag equals induced drag.
a) True
b) False
36) If an aircraft is flying at L / D maximum AOA changes its velocity, total drag will:
a) Increase
b) Remain the same
c) Decrease
37) What change in induced drag occurs as airfoil angle of attack increases in a stall?
a) Induced drag increases as lift decreases
b) Induced drag decreases as lift decreases
c) Induced drag remains constant as lift decreases
38) What is equivalent parasite area (f)?
a) The cross-sectional area of the aircraft
b) A combination of aircraft cross-sectional area presented to the relative wind and other aircraft surfaces
over which air flows.
c) The airfoil surfaces which have the same texture
d) Aircraft surfaces where parasite drag values are equal
39) Vortices can cause one or more of the wings of a trailing airplane to stall.
a) True
b) False
40) It is lees difficult for an aircraft with short wingspans (compared to the vortex generating aircraft) to counter the
imposed roll.
a) True
b) False
41) To find power required:
a) Multiply thrust required by drag
b) Multiply thrust required by velocity
c) Divide thrust required by drag
d) Divide thrust required by velocity
42) Thrust horsepower depends only on thrust and velocity.
a) True
b) False
43) Propeller efficiency (p.e.):
a) Determines power required
b) Is the ability of the engine to turn engine output into thrust
c) Is a turboprop's engine output
d) Is propeller output
44) Thrust horsepower refers to:
a) Engine output
b) Propeller output
c) The torque produced by the engine
d) None of the above
45) For a turbojet, max power excess occurs at a velocity greater than:
a) L / D
b) L / D minimum
c) L / D max
d) TAS
46) If a plane is in equilibrium flight at a constant angle of attack, an increase in weight requires:
a) A decrease in thrust required
b) An increase in thrust required
c) A decrease in power required
d) A decrease in power available
KEY
1) c
2) b
3) a
4) d
5) b
6) a
7) b
8) b
9) d
10) c
11) a
12) b
13) c
14) d
15) c
16) b
17) a
18) b
19) b
20) b
21) b
22) a
23) c
24) d
25) a
26) c
27) d
28) d
29) b
30) a
31) c
32) c
33) d
34) d
35) a
36) a
37) b
38) b
39) a
40) b
41) b
42) a
43) b
44) b
45) c
46) b