Aircraft Design Mock Test 2

10%

Question 1 of 10

1. Which of the following is correct for a jet aircraft take-off parameter (TOP)?

TOP = \(\frac{2}{σCL \frac{T}{W}}\)

TOP = \(\frac{1}{σCL \frac{T}{W}}\)

TOP = \(\frac{W}{σCL \frac{T}{W}}\)

TOP = \(\frac{W/S}{σCL \frac{T}{W}}\)

Question 1 of 10

Question 2 of 10

2. For prop aircraft at maximum range what will be the wing loading. Given CD0=0.02, aspect ratio as 8, e=0.6 and q=39.20Pa.

12.5

1.05

21.5

Question 2 of 10

Question 3 of 10

3. What is the use of V type tail?

To produce thrust

To increase wetted area

To reduce wetted area

To prevent adverse yaw roll

Question 3 of 10

Question 4 of 10

4. A/C with higher thrust to weight ratio can accelerate more quickly.

True

False

Question 4 of 10

Question 5 of 10

5. An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing.

1.021

0.25

0.9

0.121

Question 5 of 10

Question 6 of 10

6. Low wing loading will provide ___________

more space of fuel storage in cabin

less lift

more space for fuel storage in wing

less fuel storage

Question 6 of 10

Question 7 of 10

7. If root chord is 2m and tip chord is 0.9m then, find taper ratio.

0.45

0.25

0.55

0.65

Question 7 of 10

Question 8 of 10

8. The inverted V-tail is used to ______

to provide adverse yaw-roll

to increase thrust

to reduce adverse yaw-roll

to increase lift

Question 8 of 10

Question 9 of 10

9. Wing loading is ratio of ___________

lift to drag

aerodynamic force thrust to drag

reference area of wing and power of engine

weight of the aircraft and the reference area of wing

Question 9 of 10

Question 10 of 10

10. For a cambered airfoil section lift is 30N. Airfoil is operating in such way that dynamic lift is 20N. Determine the lift co-efficient for the airfoil.

0.5N

0.5

1.5N

1.5

Question 10 of 10