Aerodynamics FAA & PHAK Questions Exam

Upon reading the Pilot Handbook about Aerodynamics Flight, here are some Aerodynamics questions for a review:

1. FAA Regulations:
   • FAA regulations are listed under Title 14, entitled _.
   • A. Aeronautics and Space
   • B. Air Traffic Control
   • C. Aviation Standards
   • D. Aircraft Certification
   • Answer: A. Aeronautics and Space
2. Certification of Aviation Products:
   • The FAA certifies three types of aviation products which are _.
   • A. Aircraft
   • B. Engines
   • C. Propellers
   • D. All of the above
   • Answer: D. All of the above
3. Function of Trim Tab:
   • Functions as a trim tab to relieve control pressures and helps maintain the stabilator in the desired position.
   • Answer: Not provided.
4. Anti-Servo Tabs:
   • Moves in the same direction of the elevator.
   • Answer: A. Anti-Servo Tabs
5. Servo Tabs:
   • Moves in the opposite direction of the elevator.
   • Answer: B. Servo Tabs
6. Conventional Landing Gear:
   • Conventional landing gear is also known as _.
   • Answer: C. Tail wheel
7. Steering Aircraft:
   • Most aircraft are steered by moving the _.
   • A. Ailerons
   • B. Elevator
   • C. Rudder pedals
   • D. Flaps
   • Answer: C. Rudder pedals
8. Chemical Paint Strippers on Composites:
   • Chemical paint strippers are very harmful to composites. What should be used for paint removal from composites?
   • Answer: Only mechanical methods are allowed, such as gentle grit blasting or sanding.
9. Lightning Strike Protection:
   • Lightning strike protection for composite aircraft includes _.
   • A. Aluminum structure – good conductor
   • B. Mesh woven sa strux
   • C. Static wicks
   • D. All of the above
   • Answer: D. All of the above
10. Effect of High Density Altitude:
    • The relation of high density altitude in temperature and humidity includes _.
    • A. High temperatures
    • B. High humidity
    • C. Low temperatures
    • D. Low humidity
    • Answer: A. High temperatures
11. Stagnation Point:
    • At a point close to the leading edge, the airflow is virtually stopped (called _) and then gradually increases speed.
    • Answer: Stagnation point
12. Negative Pressure on Upper Wing Surface:
    • The _ pressure on the upper surface creates a relatively larger force on the wing than is caused by the positive pressure resulting from the air striking the lower wing surface.
    • Answer: Negative
13. Center of Pressure:
    • Aerodynamic force acts through the center of _.
    • Answer: Center of Pressure (CP)
14. Reducing Downwash:
    • How to reduce downwash?
    • A. Winglets
    • B. Tapered tip
    • Answer: A. Winglets

1. AOA for Level Flight at Low Speed:
   • To maintain level flight at low speed, the AOA should be _.
   • Answer: High
2. Changes in Drag at High AOA:
   • At high AOA, small changes in the AOA cause _ in drag.
   • Answer: High changes in drag. (Because it reached stalling angle)
3. Induced Drag with Increased Airspeed:
   • As airspeed increases, the induced drag _.
   • Answer: Decreases (Based on drag vs. velocity curve)
4. Interference Drag with Larger Angle:
   • Larger angle (between aircraft parts) = _ interference drag.
   • Answer: Lower (mas malayo mas okay)
5. Causes of Boundary Layer:
   • Causes of boundary layer include _.
   • A. Flow separation
   • B. Stall
   • C. Both A and B
   • D. None of the above
   • Answer: C. Both A and B
6. Induced Downwash vs. Downwash:
   • Induced downwash has nothing in common with the downwash that is necessary to produce lift. It is, in fact, the source of induced drag.
   • Answer: Not provided.
7. Position of Lift Vector with Less Downwash:
   • When the CG is forward of the CP, there is a natural tendency for the aircraft to want to pitch nose _.
   • Answer: Down
8. Effect of Ground Effect on Climb:
   • At ground effect, if a constant AOA is maintained, = _ effect on CL.
   • Answer: Increase
9. Aircraft Stability in Pitching:
   • Aircraft pitching has stability at _.
   • Answer: Longitudinal Stability
10. Axis for Longitudinal Stability:
    • Longitudinal stability is the quality that makes an aircraft stable about its _.
    • Answer: Lateral axis
11. Tail Load in Longitudinal Stability:
    • Downwash from the wing creates a nose _ pitching moment on the tail, which helps to keep the aircraft longitudinally stable.
    • Answer: Up (Downward tail load)
12. Tail Load to Counteract Wing Downwash:
    • What is the tail load needed to counteract wing downwash?
    • Answer: Downward tail load
13. Thrust Line Position:
    • Is the thrust line above or below CG?
    • Answer: Above
14. Effect of Keel Effect on Lateral Stability:
    • How does keel effect affect lateral stability?
    • Answer: When a high-winged aircraft is disturbed and one wing dips, the fuselage weight acts like a pendulum returning the aircraft to the horizontal level.
15. Center of Pressure vs. CG:
    • A longitudinally stable aircraft is built with the center of pressure _ of the CG.
    • Answer: Aft (Nasa harap ang CG.)
16. Dutch Roll and Lateral Stability:
    • _ lateral stability = _ directional stability.
    • Answer: Strong – weak
17. Adverse Aileron Yaw:
    • The drag difference on the two wings produces yawing opposite to a moment of rolling, known as _.
    • Answer: Adverse aileron yaw
18. Counteracting Adverse Yaw:
    • How to counteract adverse yaw (yaw left, roll right)?
    • A. Rudder deflection
    • B. Differential aileron (up aileron deflects more than down aileron)
    • C. Spoiler deflection
    • D. All of the above
    • Answer: D. All of the above
19. Proverse Yaw:
    • Spoiler def

lection also increases drag, so the wing yaws in the same direction that it rolls. It is called _.
– Answer: Proverse yaw

34. Counteracting Dutch Roll:
    • How to counter Dutch roll?
    • Answer: Yaw dampers
35. AOA Difference in Biplane Wings:
    • Difference in AOA of top and bottom wing in a biplane is known as _.
    • Answer: Decalage
36. Difference in Distance in Biplane Wings:
    • Difference in the distance of the top and bottom wing of a biplane is known as _.
    • Answer: Stagger
37. Preserving Elliptical Wing Efficiency:
    • In order to preserve the aerodynamic efficiency of the elliptical wing, rectangular and tapered wings are sometimes tailored through the use of wing _ and variation in airfoil sections until they provide as nearly as possible the elliptical wing’s lift distribution.
    • Answer: Twist
38. Bank Turn with Horizontal Lift > Centrifugal Force:
    • A bank turn where horizontal lift > centrifugal force is known as _.
    • Answer: Slipping turn
39. Bank Turn with CF > Horizontal Lift:
    • A bank turn where CF > horizontal lift is known as _.
    • Answer: Skidding turn
40. Climbing with Constant AOA:
    • If lift in steady level flight is the same as the lift in steady climb, what is needed to climb?
    • Answer: Thrust excess (Power excess)
41. Absolute Ceiling:
    • Aircraft are able to sustain a climb due to excess thrust. When the excess thrust is gone, the aircraft is no longer able to climb. At this point, the aircraft has reached its _.
    • Answer: Absolute Ceiling
42. Stalling Wing Root First:
    • How to stall wing root first?
    • A. Positive AOA or wash in sa roots
    • B. Stall strips sa roots
    • Answer: B. Stall strips sa roots
43. Aerodynamic Balance with Aft CG:
    • To balance the aircraft aerodynamically, the CL is normally located aft of the CG. Although this makes the aircraft inherently nose-heavy, _ on the horizontal stabilizer counteracts this condition.
    • Answer: Downwash
44. Thicker Airfoil and Stall AOA:
    • Thicker airfoil = stall AOA _.
    • Answer: Higher
45. Climb Propeller:
    • Propeller type with low blade angle, often called a climb propeller, provides the best performance for takeoff and climb.
    • Answer: Fixed pitch propeller
46. Cruise Propeller:
    • Propeller with a high blade angle, often called a cruise propeller, is adapted for high-speed cruise and high-altitude flight.
    • Answer: Constant pitch
47. Controllable-Pitch vs. Constant-Speed Propellers:
    • Difference between controllable-pitch propellers and constant-speed propellers.
    • Answer: Controllable – manual change, constant speed – automatic to maintain rpm
48. Higher Pitch Angle at Blade Root:
    • This propeller blade has a higher pitch angle/twist than the other.
    • Answer: Blade root – high pitch angle = low V
49. Propeller Efficiency:
    • This efficiency is the ratio of thrust horsepower to brake horsepower.
    • Answer: Propeller efficiency
50. Aircraft Turning at High Speed:
    • Aircraft turning at high speed results in _ turn rate.
    • Answer: Slower (draw arc)
51. Compensating for Added Centrifugal Force:
    • This compensates for added centrifugal force, allowing the load factor to remain the same.
    • Answer: Load factors can also be measured by an instrument called accelerometer
52. Full Application of Controls at Maneuvering Speed:
    • Full application of pitch, roll, or yaw controls should be confined to speeds below the _.
    • Answer: Va (Maneuvering speed)
53. Maximum Performance Climbing Turn:
    • The maximum performance climbing turn beginning from approximately straight-and-level flight and ending at the completion of a precise 180° turn in a wings-level, nose-high attitude at the minimum controllable airspeed is known as _.
    • Answer: Chandelles
54. Limit Load:
    • The _ is a force applied to an aircraft that causes a bending of the aircraft structure that does not return to the original shape.
    • Answer: Limit Load
55. Ultimate Load:
    • Load factor applied to the aircraft beyond the limit load and at which point the aircraft material experiences structural failure (breakage) is known as _.
    • Answer: Ultimate Load
56. Stall Speed with Forward CG:
    • Forward CG = _ stall speed.
    • Answer: Faster (FF)
57. Recovery Difficulty with Aft CG:
    • The recovery from a stall in any aircraft becomes progressively more difficult as its CG moves _.
    • Answer: Aft
58. Stalling Speed with Forward CG:
    • The aircraft stalls at a higher speed with a _ CG.
    • Answer: Forward
59. Cruising Speed with Aft CG:
    • The aircraft cruises faster with an _ CG location.
    • Answer: AFT
60. Effect of Reduced Drag with Aft CG:
    • Because of reduced drag. The drag is reduced because a smaller AOA and less downward deflection of the stabilizer are required to support the aircraft and overcome the nose-down pitching tendency.
    • Answer: Not provided.
61. Delaying Shock Wave Induced Flow Separation:
    • Used to delay or prevent shock wave-induced boundary layer separation encountered in transonic flight.
    • Answer: Vortex Generators
62. Shock Wave:
    • Forms as a boundary between the supersonic and subsonic ranges.
    • Answer: Shock wave
63. Wave Drag:
    • The drag incurred in the transonic region due to shock wave formation and airflow separation is known as _.
    • Answer: Wave drag
64. Effect of Downwash on Horizontal Tail:
    • Thus, an increase in downwash _ the horizontal tail’s pitch control effectiveness.
    • Answer: Decreases
65. Nose Down Effect at Transonic Region:
    • At the transonic region, the aircraft will nose down, known as _.
    • Answer: Mach tuck
66. Delaying Shock Wave Induced Flow Separation (Alternate Method):
    • How to delay shock wave-induced flow separation?
    • Answer: Swept-back wing theory – air flow perpendicular to the LE is slower, thus the aircraft can go faster without the formation of a shockwave.
67. Decrease in Static Lateral Stability:
    • Which type of wing arrangement decreases the static lateral stability of an aeroplane?
    • A. Increased wing span
    • B. Anhedral
    • Answer: Anhedral