Module8.4.1High Speed Airflow(1of3)

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1. Is the Mach number range for transonic flight?

Mach 0.8 to 1.2

Mach 1.2 to 5.0

Mach 0.8 to 1.3

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2. Which of the following statements is true about subsonic flight?

Airflow is entirely compressible

Airflow remains smooth with gradual pressure changes

Shock waves are present on the wings

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3. What is the primary aerodynamic challenge in transonic flight?

Sudden increase in drag due to shock waves

Total loss of lift

Increase in stability

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4. Why do supersonic aircraft have sharp leading edges?

To reduce parasite drag

To minimize shock wave formation

To increase lift

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5. What happens when an aircraft reaches the speed of sound?

Induced drag disappears

The aircraft’s lift doubles

A shock wave forms around the aircraft

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6. The speed of sound at sea level (15°C) is approximately:

350 m/s

320 m/s

340 m/s

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7. How does altitude affect the speed of sound?

It increases with increasing altitude

It remains constant

It decreases with decreasing temperature

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8. An aircraft flying at 510 m/s where the local speed of sound is 300 m/s has a Mach number of:

Mach 2.0

Mach 0.9

Mach 1.7

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9. What is the term for the speed at which local airflow first becomes supersonic?

Threshold Mach number

Maximum Mach number

Critical Mach number

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10. If an aircraft is flying at Mach 0.75, it is in which speed regime?

Supersonic

Subsonic

Transonic

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11. The major issue in transonic flight is:

Formation of shock waves and drag rise

Increase in stability

Increased lift

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12. What aerodynamic phenomenon is experienced at Mach 1?

Increase in parasite drag

Formation of a sonic boom

No change in pressure distribution

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13. A supersonic aircraft will experience:

Only subsonic flow around the aircraft

No shock waves

Supersonic flow over all surfaces

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14. What is the main advantage of supersonic flight?

Reduced travel time

Higher lift

Decreased fuel consumption

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15. What type of wave forms at transonic speeds due to airflow separation?

Compression wave

Shock wave

Expansion wave

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16. What type of shock wave is perpendicular to airflow?

Oblique shock wave

Normal shock wave

Expansion wave

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17. What effect do shock waves have on airflow?

Decrease in density

Sudden increase in pressure and temperature

Increase in velocity

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18. What is compressibility buffet?

A reduction in thrust

Increased lift production

An aerodynamic instability due to shock waves

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19. How do oblique shock waves differ from normal shock waves?

They completely stop the airflow

They are angled and allow smoother pressure transition

They are weaker and do not affect pressure

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20. Where does the strongest shock wave form in supersonic flight?

At the trailing edge

At the nose of the aircraft

At the wingtips

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