Aircraft Design Practice Test 10

1. Determine required static margin if lift curve slope is 6.5 per rad and pitching moment coefficient slope as -0.58 per rad.

2. Consider the aircraft with weight of 1234 kg. Find the approximate value of the damping ratio if time taken by system for damping is minimum.

3. Which of the following is required condition of thrust required minimum?

4. Which of the following is correct?

5. A wing alone aircraft has aerodynamic centre pitching moment coefficient of -0.126. If lift coefficient at zero AOA is 0.38 then, find Cm0. Consider Xcg=0.3.

6. Aircraft can suffer from adverse yaw during rolling.

7. An aircraft is designed to be in steady level flight with weight of 1500N and CL of 1.0. Determine at which speed we need to design this aircraft so that it can achieve this requirement. Consider density as 1.2 kg/m³ and reference area as 2m².

8. An aircraft wing is experiencing AOA of 5°. If downwash due to wing is 2.6° then, how much angle is being seen by tail of the aircraft?

9. Determine the net velocity if sideslip angle is 3.8 degree and [v] = 4.2 unit.

10. Damping ratio is defined as __________