Aircraft Design Mock Test 10

10%

Question 1 of 10

1. For a typical gliding flight, thrust will be ________

always same as weight

equal to the lift

zero

always same as drag

Question 1 of 10

Question 2 of 10

2. Determine static pressure if external flow dynamic pressure is 1800psf and flow has Mach number of 2.

642.857psf

2400 psf

1000psf

4673 psf

Question 2 of 10

Question 3 of 10

3. If a Maneuver requires specific power of 1200 unit then, find the approximate value of fuel specific energy. Given thrust as 1000 unit and tsfc of 0.00042 unit.

1568.45 unit

2857.14 unit

4500 unit

6789 unit

Question 3 of 10

Question 4 of 10

4. Determine the value of climb angle if, excess thrust is 40 unit and weight of the aircraft is 60 unit. Consider steady climb.

41.8

Question 4 of 10

Question 5 of 10

5. The distance shown by '?' in the following diagram is termed as __________

loiter

flare distance

climb

cruise

Question 5 of 10

Question 6 of 10

6. An aircraft is in sustained turn with thrust loading of 0.8 and aerodynamic efficiency of 6. Determine the approximate value of maximum load factor.

4.8

Question 6 of 10

Question 7 of 10

7. Total energy divided by the aircraft weight is term as ____________

Total energy

Specific energy

Question 7 of 10

Question 8 of 10

8. Find lift to weight ratio if climb angle is 45°.

0.707

0.992

1.34

Question 8 of 10

Question 9 of 10

9. Velocity for the best glide ratio is 100ft/s. Determine velocity for minimum sink rate.

76ft/s

45 fts²

124m/s

23fts

Question 9 of 10

Question 10 of 10

10. Determine the value of turn rate. Consider glider has centripetal acceleration of 10 and velocity of 9.5.

2.8

9.5

1.052

Question 10 of 10