Free UK CAA Part-66 Module 8 — Basic Aerodynamics (B1.1) Practice Questions

Sample Practice Questions

Try these 10 sample questions from the UK CAA Part-66 Module 8 — Basic Aerodynamics (B1.1) practice bank. Each includes the answer and explanation. Continue with the interactive practice above to review the full question set.

1. 1Why is a standard atmosphere used when comparing aircraft performance measured on different days?

   1. A.It supplies a common set of reference conditions.Correct answer: A
   2. B.It predicts the exact weather for each flight.
   3. C.It removes the influence of air density on lift.
   4. D.It makes pressure independent of altitude.

   Explanation: The FAA explains: "Due to the changing atmospheric pressure, a standard reference was developed." A common reference allows performance results to be compared despite changing atmospheric conditions. It does not forecast weather or eliminate physical density and pressure effects.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Principles of Flight — Chapter 4, p. 4-3, Atmospheric Pressure

2. 2In the terminology used to describe an aerofoil section, what does camber describe?

   1. A.The distance between the two wingtips
   2. B.The curvature of the aerofoil surfacesCorrect answer: B
   3. C.The angle between chord and relative airflow
   4. D.The distance between the wing and tail

   Explanation: The handbook states: "The camber of a wing is the curvature which is present on top and bottom surfaces." Camber concerns surface curvature. Span, angle of attack, and wing-to-tail distance are different geometric properties.

   Reference: FAA Aviation Maintenance Technician Handbook — General — Chapter 5, p. 5-38, Camber

3. 3An aircraft maintains straight, level, unaccelerated flight. Assume thrust and drag act horizontally and neglect tail-load effects. Which force relationship applies?

   1. A.Lift equals drag; thrust equals weight.
   2. B.Lift exceeds weight; thrust equals drag.
   3. C.Lift equals weight; thrust equals drag.Correct answer: C
   4. D.Lift equals weight; thrust exceeds drag.

   Explanation: The source states: "in straight, level, unaccelerated flight, it is true that the opposing lift/weight forces are equal." Vertical and horizontal resultant forces must each be zero under the stated assumptions. Thus lift balances weight and thrust balances drag; no equality between lift and drag is required.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Aerodynamics of Flight — Chapter 5, Forces Acting on the Aircraft

4. 4After a small pitch disturbance is removed, an aircraft initially tends to move back toward its trimmed condition. Which characteristic does this initial tendency demonstrate?

   1. A.Neutral static stability
   2. B.Negative static stability
   3. C.Positive static stabilityCorrect answer: C
   4. D.Neutral dynamic stability

   Explanation: The handbook states: "Positive static stability—the initial tendency of the aircraft to return to the original state of equilibrium after being disturbed." The initial restoring tendency establishes positive static stability. It does not, by itself, establish the eventual damping of any oscillations.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Aerodynamics of Flight — Chapter 5, Static Stability

5. 5What is the standard sea-level air temperature in the International Standard Atmosphere?

   1. A.0 °C
   2. B.15 °CCorrect answer: B
   3. C.25 °C
   4. D.59 °C

   Explanation: The handbook states: "The standard atmosphere at sea level is a surface temperature of 59 °F or 15 °C". The Celsius value is 15; 59 is its Fahrenheit equivalent, not its Celsius value.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Principles of Flight — Chapter 4, p. 4-3, Atmospheric Pressure

6. 6Which line is the chord line of an aerofoil section?

   1. A.A curved line midway between its upper and lower surfaces
   2. B.A line along the wing's span between the two wingtips
   3. C.A line joining the aircraft's nose to its centre of gravity
   4. D.A straight line joining its leading and trailing edgesCorrect answer: D

   Explanation: The handbook states: "The chord line is an imaginary straight line running from the wing’s leading edge to its trailing edge." The chord is straight and joins the section's edges. The curved midline is the mean camber line; span and aircraft reference lines are different.

   Reference: FAA Aviation Maintenance Technician Handbook — General — Chapter 5, p. 5-38, Chord Line

7. 7An aircraft of mass 1,000 kg has 3,000 N of forward thrust and 2,000 N of drag. Neglect other forces along its straight flight path. What is its forward acceleration?

   1. A.1.0 m/s²Correct answer: A
   2. B.2.0 m/s²
   3. C.3.0 m/s²
   4. D.5.0 m/s²

   Explanation: The PHAK states: "As long as the thrust continues to be greater than the drag, the aircraft continues to accelerate." The maintenance handbook gives "Force = Mass × Acceleration". Net force = 3,000 − 2,000 = 1,000 N. Therefore a = Fnet/m = 1,000 N ÷ 1,000 kg = 1.0 m/s² forward. 2.0 uses drag alone, 3.0 uses thrust alone, and 5.0 adds opposing forces.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Aerodynamics of Flight — Chapter 5, Thrust

8. 8A displaced aircraft develops no initial restoring or diverging tendency and remains at the new attitude after the disturbing force is removed. How is its static stability classified?

   1. A.NeutralCorrect answer: A
   2. B.Positive
   3. C.Negative
   4. D.Damped

   Explanation: The handbook states: "Neutral static stability—the initial tendency of the aircraft to remain in a new condition after its equilibrium has been disturbed." Remaining at the displaced condition is neutral static stability. Positive stability restores, negative stability diverges, and damping describes a time-dependent response.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Aerodynamics of Flight — Chapter 5, Static Stability

9. 9Which value is approximately the ISA sea-level atmospheric pressure, expressed in hectopascals?

   1. A.299.2 hPa
   2. B.760.0 hPa
   3. C.1013.2 hPaCorrect answer: C
   4. D.1470.0 hPa

   Explanation: The FAA gives standard sea-level pressure as "14.70 pounds per square inch (psi) of surface, or 1,013.2 millibars (mb)." A millibar equals a hectopascal, giving approximately 1013.2 hPa. The other values confuse units or decimal positions.

   Reference: FAA Pilot’s Handbook of Aeronautical Knowledge — Principles of Flight — Chapter 4, p. 4-3, Atmospheric Pressure

10. 10A swept, tapered wing has different local chord lengths along its span. Which term identifies its representative aerodynamic chord?

    1. A.Mean aerodynamic chordCorrect answer: A
    2. B.Wingtip chord alone
    3. C.Maximum wing thickness
    4. D.Wing span alone

    Explanation: The handbook states: "In relation to the aerodynamics of the wing, the average length of the chord on these tapered swept-back wings is known as the mean aerodynamic chord (MAC)." MAC is the representative aerodynamic chord, rather than simply the tip chord, thickness, or span. The question concerns the named reference, not a formula for calculating a tapered wing's MAC.

    Reference: FAA Aviation Maintenance Technician Handbook — General — Chapter 6, p. 6-28, Mean Aerodynamic Chord