Aircraft Design Mock Test 8

10%

Question 1 of 10

1. What do you mean by overall pressure ratio?

Stagnation pressure divided by dynamic pressure

Ratio of dynamic to normal pressure

Ratio of pressure at engine exhaust and inlet front face

Total pressure divided by stagnation pressure

Question 1 of 10

Question 2 of 10

2. My aircraft is flying at particular altitude. At that altitude ratio of actual airspeed to the equivalent airspeed is 1.4 then, what should be the desire value of density ratio?

0.189

1.89

0.12

0.51

Question 2 of 10

Question 3 of 10

3. Engine manufacturer has provided the reference value of inlet pressure recovery as 0.94. If actual pressure recovery is found to be 0.91 then, find the thrust loss. Consider C of 1.25.

0.0375

0.568

0.0865

0.123

Question 3 of 10

Question 4 of 10

4. If stain in body is 0.01 in longitudinal direction and has length of 52 mm then, find the deformation in length of the body.

22mm

0.52mm

Question 4 of 10

Question 5 of 10

5. Propulsive efficiency is defined as _____________

lift required to thrust required at each segment

aerodynamic efficiency

ratio of obtained thrust power to energy expanded

thrust used by compressed energy

Question 5 of 10

Question 6 of 10

6. Turbofan engine uses a large fan at inlet to ________

increase tailplane lift

increase flow velocity

increase wing tip lift

increase efficiency of the engine

Question 6 of 10

Question 7 of 10

7. Flat plate skin friction coefficient depends upon _____________

mach number, reynolds number etc

reynolds number only

mach number only

weight of the aircraft

Question 7 of 10

Question 8 of 10

8. When an aircraft flies in air, it experiences _________

only drag force

lift, drag, thrust loads, etc

only lift load

only gust load

Question 8 of 10

Question 9 of 10

9. The actual available thrust used in performance calculations is termed as __________

installed net propulsive force

installed weight to reference area

lift to drag ratio

gross lift and weight

Question 9 of 10

Question 10 of 10

10. Thrust generated by an engine is proportional to mass flow rate.

False

True

Question 10 of 10