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100+ Free CAAS SAR-66 Module 8 (Basic Aerodynamics) Practice Questions
CAAS SAR-66 Category B1/B2 Basic Knowledge Examination - Module 8 Basic Aerodynamics practice questions are available now; exam metadata is being verified.
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2026 Statistics
Key Facts: CAAS SAR-66 Module 8 (Basic Aerodynamics) Exam
20 Qs
Total multiple-choice questions on official exam.
CAAS AC 66-13 Syllabus Guidelines
25 Mins
Time allotted for Module 8 exam.
CAAS AC 66-13 Category B1/B2 Schedule
75%
Minimum required passing score.
CAAS SAR-66 Appendix 1 Regulations
S$87.20
Exam fee per basic knowledge subject.
Air Navigation Order Twelfth Schedule (from 1 Jan 2026)
Module 8
Basic Aerodynamics syllabus requirement.
CAAS SAR-66 / EASA Part-66 Syllabus
CAAS SAR-66 Module 8 is a 20-question, 25-minute examination requiring a 75% passing score for CAAS Category B1 and B2 Aircraft Maintenance Engineer licensing in Singapore.
Sample CAAS SAR-66 Module 8 (Basic Aerodynamics) Practice Questions
Try these sample questions to test your CAAS SAR-66 Module 8 (Basic Aerodynamics) exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.
1According to the International Standard Atmosphere (ISA), what are the standard sea-level temperature, pressure, and air density values?
A.+15°C (288.15 K), 1013.25 hPa (29.92 inHg), and 1.225 kg/m³
B.+20°C (293.15 K), 1000.00 hPa (29.53 inHg), and 1.000 kg/m³
C.+0°C (273.15 K), 1013.25 hPa (29.92 inHg), and 1.292 kg/m³
D.+15°C (288.15 K), 1030.00 hPa (30.42 inHg), and 1.150 kg/m³
Explanation: The International Standard Atmosphere (ISA) defines standard sea-level values as a temperature of +15°C (288.15 K), a static pressure of 1013.25 hPa (equivalent to 29.92 inHg or 760 mmHg), and a mass density of 1.225 kg/m³. These baseline values serve as the international aviation reference for calibrating instruments and calculating aircraft aerodynamic performance under standard conditions.
2Using the ISA standard temperature lapse rate of 1.98°C per 1,000 ft in the troposphere, what is the standard ISA temperature at an altitude of 10,000 ft?
A.-4.8°C
B.-19.8°C
C.+4.8°C
D.-14.8°C
Explanation: In the ISA troposphere, temperature decreases uniformly at a standard lapse rate of 1.98°C per 1,000 ft (or 6.5°C per 1,000 m) up to the tropopause. Starting from the sea-level standard of +15°C: T = 15°C - (1.98°C × 10) = 15°C - 19.8°C = -4.8°C. Thus, the standard ISA temperature at 10,000 ft is -4.8°C.
3What is the ISA standard outside air temperature at an altitude of 15,000 ft?
A.-14.7°C
B.-29.7°C
C.-4.7°C
D.+0.3°C
Explanation: Applying the ISA temperature lapse rate of 1.98°C per 1,000 ft from the sea-level value of +15°C: T = 15°C - (1.98°C × 15) = 15°C - 29.7°C = -14.7°C. Therefore, at 15,000 ft altitude in standard conditions, the air temperature is -14.7°C.
4Calculate the ISA standard temperature at an altitude of 20,000 ft.
A.-24.6°C
B.-39.6°C
C.-14.6°C
D.-20.0°C
Explanation: The formula for ISA temperature below 36,089 ft is T = 15°C - (1.98°C × Altitude in thousands of feet). At 20,000 ft: T = 15 - (1.98 × 20) = 15 - 39.6 = -24.6°C. The standard temperature at 20,000 ft is therefore -24.6°C.
5At what altitude in the International Standard Atmosphere (ISA) does the tropopause begin, and what happens to temperature above this boundary up to 20 km (65,617 ft)?
A.36,089 ft (11 km); temperature remains constant at -56.5°C
B.30,000 ft (9.1 km); temperature increases at 2.0°C per 1,000 ft
C.45,000 ft (13.7 km); temperature continues decreasing down to -80.0°C
D.25,000 ft (7.6 km); temperature drops to 0°C and stays isothermal
Explanation: In ISA, the tropopause marks the boundary between the troposphere and stratosphere at an altitude of 36,089 ft (11 km). Above 36,089 ft up to 20 km (65,617 ft), the lower stratosphere is isothermal, meaning the temperature remains constant at -56.5°C (216.65 K).
6What is the approximate rate of atmospheric static pressure decrease near sea level per 1,000 ft of altitude gain?
A.1.0 inHg (approx. 30 hPa or 1 psi) per 1,000 ft
B.3.0 inHg (approx. 100 hPa) per 1,000 ft
C.0.25 inHg (approx. 10 hPa) per 1,000 ft
D.5.0 inHg (approx. 150 hPa) per 1,000 ft
Explanation: Near sea level in lower troposphere, atmospheric static pressure decreases at a rule-of-thumb rate of approximately 1.0 inHg (or about 30 hPa / 1 hPa per 30 ft) for every 1,000 ft of ascent. As altitude increases, this rate of pressure drop decreases because air becomes progressively less dense.
7If the Outside Air Temperature (OAT) at an altitude of 10,000 ft is measured at -10.0°C, what is the ISA temperature deviation at this flight level?
A.ISA -5.2°C
B.ISA +5.2°C
C.ISA -10.0°C
D.ISA +15.0°C
Explanation: Standard ISA temperature at 10,000 ft is 15°C - (1.98°C × 10) = -4.8°C. ISA temperature deviation is calculated as Actual Temperature minus ISA Standard Temperature: Deviation = -10.0°C - (-4.8°C) = -5.2°C. Thus, conditions are ISA -5.2°C (5.2°C colder than standard).
8How does an increase in air temperature at constant static pressure affect air density and aircraft aerodynamic performance?
A.Air density decreases, reducing both lift generation and engine thrust
B.Air density increases, enhancing wing lift and engine efficiency
C.Air density remains constant because pressure is unchanged
D.Air density decreases, which increases wing lift due to higher particle kinetic energy
Explanation: According to the Ideal Gas Law (ρ = P / (R × T)), air density is inversely proportional to absolute temperature. When temperature increases at constant pressure, air expands and becomes less dense. Lower air density reduces mass flow over wings and through engines, thereby decreasing lift generation and propulsive thrust.
9Why does high atmospheric humidity reduce air density compared to dry air at the same temperature and pressure?
A.Water vapor molecules (H₂O) have a lower molecular weight than dry air molecules (N₂ and O₂)
B.Water vapor molecules absorb air pressure, reducing total atmospheric mass
C.Humidity increases air viscosity, forcing air molecules further apart
D.Water vapor binds with nitrogen to form heavier compounds that settle near the surface
Explanation: Water vapor (H₂O) has a molecular weight of approximately 18 g/mol, whereas dry air (composed primarily of N₂ and O₂) has an average molecular weight of approximately 29 g/mol. According to Avogadro's law, equal volumes of gas contain equal numbers of molecules; replacing dry air molecules with lighter water vapor molecules reduces overall air density.
10What is the definition of Pressure Altitude?
A.The altitude indicated when the altimeter sub-scale is set to 1013.25 hPa (29.92 inHg)
B.The actual vertical distance of the aircraft above mean sea level (MSL)
C.The vertical distance of the aircraft above the immediate terrain (AGL)
D.The pressure altitude corrected for non-standard outside air temperature
Explanation: Pressure Altitude is defined as the height above the Standard Datum Plane (1013.25 hPa or 29.92 inHg). It is the altitude indicated on a pressure altimeter when its sub-scale is adjusted to the standard sea-level reference pressure.
About the CAAS SAR-66 Module 8 (Basic Aerodynamics) Practice Questions
Verified exam format metadata for CAAS SAR-66 Category B1/B2 Basic Knowledge Examination - Module 8 Basic Aerodynamics is pending. The practice questions above remain available while official exam length, timing, passing score, fee, and administrator details are reviewed.