TECHNICAL GENERAL (CPL) USAV104 F.Y.B.Sc Aviation University Of
Mumbai Q&A Practice Quiz
1. The angle between the aeroplane longitudinal axis and the chord line is the:
• Angle of incidence
2. Maintaining thickness/chord ratio but changing to a supercritical wing section will:
• Give the aircraft an increased range
3. Assuming ISA conditions, which statement with respect to the climb is correct?
• At constant IAS the Mach number increases
4. The point about which the wing pitching moment is independent of angle of attack is
called
• The aerodynamic centre
5. The unit of measurement of pressure is:
• psi
6. The unit of density is:
• kg/m3
7. The angle of attack of a wing profile is defined as the angle between:
• The undisturbed airflow and the chordline
8. Wing loading is:
• The ratio of aircraft weight to wing area
, 9. The term angle of attack is defined as:
• The angle between the wing chord line and the relative wind
10. At a constant IAS, induced drag is affected by:
• Aircraft weight
11. What is the effect on EAS as height is increased when you are holding a constant IAS?
• EAS falls
12. At a constant CAS when flying below sea level an aircraft will have:
• A lower TAS than at sea level at ISA conditions
13. The angle of attack of a two dimensional wing section is the angle between:
• The chord line of the aerofoil and the free stream direction
14. The units of wing loading and dynamic pressure q are:
• N/m2
15. What is the MAC of a wing?
• The same as the mean chord of a rectangular wing of the same span
16. A symmetrical aerofoil section at CL = 0 will produce?
• Zero pitching moment
17. The CP on a swept wing aircraft will move forward due to:
• Up stall of the wing
Mumbai Q&A Practice Quiz
1. The angle between the aeroplane longitudinal axis and the chord line is the:
• Angle of incidence
2. Maintaining thickness/chord ratio but changing to a supercritical wing section will:
• Give the aircraft an increased range
3. Assuming ISA conditions, which statement with respect to the climb is correct?
• At constant IAS the Mach number increases
4. The point about which the wing pitching moment is independent of angle of attack is
called
• The aerodynamic centre
5. The unit of measurement of pressure is:
• psi
6. The unit of density is:
• kg/m3
7. The angle of attack of a wing profile is defined as the angle between:
• The undisturbed airflow and the chordline
8. Wing loading is:
• The ratio of aircraft weight to wing area
, 9. The term angle of attack is defined as:
• The angle between the wing chord line and the relative wind
10. At a constant IAS, induced drag is affected by:
• Aircraft weight
11. What is the effect on EAS as height is increased when you are holding a constant IAS?
• EAS falls
12. At a constant CAS when flying below sea level an aircraft will have:
• A lower TAS than at sea level at ISA conditions
13. The angle of attack of a two dimensional wing section is the angle between:
• The chord line of the aerofoil and the free stream direction
14. The units of wing loading and dynamic pressure q are:
• N/m2
15. What is the MAC of a wing?
• The same as the mean chord of a rectangular wing of the same span
16. A symmetrical aerofoil section at CL = 0 will produce?
• Zero pitching moment
17. The CP on a swept wing aircraft will move forward due to:
• Up stall of the wing
