100+ Free Aeronautical Engineering Practice Questions

Pass your PRC Aeronautical Engineer Licensure Examination (Philippines) exam on the first try — instant access, no signup required.

✓ No registration✓ No credit card✓ No hidden fees✓ Start practicing immediately

100+ Questions

100% Free

Loading practice questions...

Same family resources

Explore More Philippines PRC Engineering Exams

Continue into nearby exams from the same family. Each card keeps practice questions, study guides, flashcards, videos, and articles in one place.

2026 Statistics

Key Facts: Aeronautical Engineering Exam

75%

Required weighted general average score to pass

PRC Board Guidelines

3 Days

Duration of the full licensing board examination

PRC Examination Schedule

The PRC Aeronautical Engineer Licensure Examination is the licensing board exam in the Philippines evaluating aerodynamics, structures, propulsion, and regulations. This free 100-question practice bank provides comprehensive board-style prep.

Sample Aeronautical Engineering Practice Questions

Try these sample questions to test your Aeronautical Engineering exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1Which of the following describes the relation between the lift coefficient (Cl) and the angle of attack (alpha) for a symmetric airfoil in the linear range?

A.Cl is zero at zero angle of attack and increases linearly with a slope of approximately 2*pi per radian.

B.Cl is positive at zero angle of attack and increases quadratically with alpha.

C.Cl is negative at zero angle of attack and decreases linearly with a slope of -2*pi per radian.

D.Cl is zero at zero angle of attack and remains constant regardless of the angle of attack.

Explanation: According to thin airfoil theory, a symmetric airfoil has zero lift at zero angle of attack (alpha = 0). The lift curve slope (dCl/dalpha) in the linear region is theoretical 2*pi per radian (approximately 0.11 per degree). This linear relationship holds until the airfoil approaches the stall angle where flow separation occurs.

2According to Bernoulli's equation for inviscid, incompressible flow, what happens to the static pressure of a fluid when its velocity increases along a streamline?

A.The static pressure remains constant because total pressure changes.

B.The static pressure decreases to balance the increase in dynamic pressure.

C.The static pressure increases proportionally to the square of the velocity.

D.The static pressure drops to zero immediately when any flow is initiated.

Explanation: Bernoulli's equation states that for a steady, incompressible, frictionless flow, the total pressure (the sum of static pressure and dynamic pressure) is constant along a streamline. Dynamic pressure is defined as 0.5 * rho * V^2. Therefore, as velocity increases, dynamic pressure increases, requiring a corresponding decrease in static pressure to maintain a constant total pressure.

3For a steady, incompressible, one-dimensional flow through a diverging duct, how do the velocity and volumetric flow rate change along the duct?

A.Velocity increases and the volumetric flow rate increases.

B.Velocity decreases and the volumetric flow rate remains constant.

C.Velocity remains constant and the volumetric flow rate decreases.

D.Velocity decreases and the volumetric flow rate decreases.

Explanation: By the continuity equation for incompressible flow, the volumetric flow rate (Q = A * V) must remain constant at all sections of the duct. In a diverging duct, the cross-sectional area (A) increases along the flow direction. To keep the product of area and velocity constant, the flow velocity (V) must decrease.

4The pressure coefficient (Cp) at a point on an airfoil in incompressible flow is defined in terms of static pressure (p), free-stream static pressure (p_inf), and free-stream dynamic pressure (q_inf). What is the value of Cp at a stagnation point?

A.Cp is equal to 0.

B.Cp is equal to 1.

C.Cp is equal to -1.

D.Cp is equal to infinity.

Explanation: The pressure coefficient is defined as Cp = (p - p_inf) / q_inf. At a stagnation point, the flow velocity is decelerated to zero, which means the local static pressure (p) reaches the total pressure (p_t). Since total pressure equals p_inf + q_inf for incompressible flow, substituting p = p_inf + q_inf into the Cp equation yields Cp = 1.

5If the ambient temperature at a specific flight altitude is -40 degrees Celsius, what is the speed of sound at this altitude? (Assume air behaves as a perfect gas with gamma = 1.4 and R = 287 J/kg*K)

A.Approximately 340.3 m/s

B.Approximately 306.0 m/s

C.Approximately 243.2 m/s

D.Approximately 150.0 m/s

Explanation: The speed of sound in a perfect gas is calculated using the formula a = sqrt(gamma * R * T), where T is the absolute temperature in Kelvin. Converting -40 degrees Celsius to Kelvin gives T = 273.15 - 40 = 233.15 K. Calculating the speed of sound: a = sqrt(1.4 * 287 * 233.15) = sqrt(93679.67) = 306.07 m/s.

6An aircraft is flying at a true airspeed of 600 knots at an altitude where the local speed of sound is 580 knots. Which Mach regime describes this flight condition?

A.Subsonic flow

B.Transonic flow

C.Supersonic flow

D.Hypersonic flow

Explanation: The Mach number (M) is the ratio of true airspeed (V) to the local speed of sound (a). Here, M = 600 / 580 = 1.034. Since the Mach number is greater than 1.0 but less than 5.0, the flight condition is classified as supersonic. Transonic flow generally refers to the range of M = 0.8 to 1.2 where both subsonic and supersonic regions exist on the airframe, but a steady state condition with M > 1.0 is strictly supersonic.

7What is the standard temperature lapse rate in the troposphere according to the U.S. Standard Atmosphere (which is also adopted by ICAO)?

A.-6.5 degrees Celsius per kilometer (-0.0065 K/m)

B.-1.0 degree Celsius per kilometer (-0.0010 K/m)

C.0 degrees Celsius per kilometer (isothermal)

D.3.2 degrees Celsius per kilometer (0.0032 K/m)

Explanation: In the standard atmosphere, the troposphere has a constant temperature lapse rate (beta) of -6.5°C per kilometer (equivalent to -1.98°C per 1,000 feet or -0.0065 K/m). This linear decrease of temperature with altitude continues up to the tropopause, which is defined at an altitude of 11,000 meters (36,089 feet).

8At what altitude does the tropopause begin in the ICAO Standard Atmosphere, separating the troposphere from the stratosphere?

A.11,000 meters (36,089 feet)

B.20,000 meters (65,617 feet)

C.32,000 meters (104,987 feet)

D.8,000 meters (26,247 feet)

Explanation: In the standard atmospheric model, the tropopause marks the boundary where the temperature stops decreasing linearly and becomes constant (isothermal) at -56.5°C (216.65 K). This boundary is defined to occur at an altitude of exactly 11,000 meters (36,089 feet) above sea level.

9The density ratio (sigma) is the ratio of local air density (rho) at altitude to the standard sea-level air density (rho_0). If the density ratio is 0.5328, what physical effect does this have on aerodynamic lift if velocity is held constant?

A.Lift will increase because the air is thinner and flows faster.

B.Lift will decrease to approximately 53.28% of its sea-level value.

C.Lift will remain unchanged because lift only depends on velocity.

D.Lift will drop to zero because air must have standard density to generate lift.

Explanation: The aerodynamic lift equation is L = 0.5 * rho * V^2 * S * Cl. At altitude, the air density is rho = sigma * rho_0. If the velocity (V), wing area (S), and lift coefficient (Cl) are held constant, lift is directly proportional to density. Therefore, a density ratio (sigma) of 0.5328 reduces the lift generated to exactly 53.28% of what it would be at sea level under identical flight parameters.

10Which of the following equations represents the coefficient of induced drag (Cdi) for a finite wing with a 3D lift coefficient (CL), aspect ratio (AR), and Oswald efficiency factor (e)?

A.Cdi = CL / (pi * e * AR)

B.Cdi = CL^2 / (pi * e * AR)

C.Cdi = CL^2 * pi * e * AR

D.Cdi = Cd0 + CL^2 / (pi * e * AR)

Explanation: Induced drag is the drag resulting from the generation of lift on a finite wing, which creates wingtip vortices and downwash. The formula for the induced drag coefficient is Cdi = CL^2 / (pi * e * AR). This shows that induced drag increases quadratically with the lift coefficient and decreases with higher aspect ratios.

About the Aeronautical Engineering Exam

The PRC Aeronautical Engineer Licensure Examination is the professional licensing exam for aeronautical engineers in the Philippines. It evaluates candidates on their proficiency in aerodynamics, aircraft structures, aircraft propulsion, flight mechanics, aircraft design, and aviation laws and regulations. Passing this exam grants registration and license to practice as an aeronautical engineer.

Assessment

Three-day board examination consisting of multiple-choice questions across core aeronautical engineering subjects.

Time Limit

Three days (varying hours per subject paper)

Passing Score

A weighted general average of at least 75%, with no grade below 50% in any subject paper.

Exam Fee

Standard PRC application and examination fees apply. (Professional Regulation Commission (PRC) - Board of Aeronautical Engineering)

Aeronautical Engineering Exam Content Outline

25%

Aerodynamics

Fundamentals of low-speed and high-speed aerodynamics, wind tunnels, and flight mechanics.

25%

Aircraft Structures and Design

Stress analysis, load paths, structural dynamics, materials, and aircraft design principles.

25%

Aircraft Propulsion

Piston engines, gas turbine engines, rockets, propellants, and fuel systems.

25%

Aircraft Maintenance and Regulations

Aviation laws, maintenance practices, instrument systems, and civil aviation regulations.

How to Pass the Aeronautical Engineering Exam

What You Need to Know

Passing score: A weighted general average of at least 75%, with no grade below 50% in any subject paper.
Assessment: Three-day board examination consisting of multiple-choice questions across core aeronautical engineering subjects.
Time limit: Three days (varying hours per subject paper)
Exam fee: Standard PRC application and examination fees apply.

Keys to Passing

Complete 500+ practice questions
Score 80%+ consistently before scheduling
Focus on highest-weighted sections
Use our AI tutor for tough concepts

Aeronautical Engineering Study Tips from Top Performers

1Focus on core aerodynamic formulas, lift-drag calculations, and aircraft performance tables.

2Review basic thermodynamics for propulsion and aircraft engine cycle calculations.

3Familiarize yourself with civil aviation regulations (CAR) and aviation laws in the Philippines.

Frequently Asked Questions

What are the requirements to take the Aeronautical Engineering board exam?

You must be a graduate of BS Aeronautical Engineering from a recognized school, and submit the required PRC application documents.

What is the passing score for the exam?

You must achieve a weighted general average of at least 75%, with no grade below 50% in any subject paper.

100+ Free Aeronautical Engineering Practice Questions

Explore More Philippines PRC Engineering Exams

PRC Agricultural and Biosystems Engineer Licensure Examination

PRC Chemical Engineer Licensure Examination

PRC Chemist Licensure Examination

PRC Civil Engineering Licensure Examination

PRC Electrical Engineering Licensure Examination

PRC Electronics Engineering Licensure Examination