Q.1
If area ratio is 1.then, at which mach number flow is flowing?
  • a) 0.68
  • b) 1.89
  • c) 2
  • d) 0.21
Q.2
What is the function of a typical nozzle?
  • a) To expand exhaust flow
  • b) To reduce flow velocity
  • c) To generate lift to fly
  • d) To increase pressure
Q.3
Performance of engine can be controlled by nozzle.
  • a) True
  • b) False
Q.4
Following diagram represents ______________
Questionaircraft-design-questions-answers3.jpg
  • a) fixed convergent nozzle
  • b) fixed divergent nozzle
  • c) cd nozzle
  • d) rocket engine
Q.5
Only convergent section will be used for supersonic speeds.
  • a) True
  • b) False
Q.6
Consider a flow with 0.5M. Now, as area decreases, velocity of the flow inside convergent section _____________
  • a) increases
  • b) decreases
  • c) reduces by half always
  • d) velocity is independent of area
Q.7
Following diagram represents ___________
Questionaircraft-design-questions-answers6.jpg
  • a) preliminary sizing of capture area
  • b) lift curve
  • c) drag polar
  • d) drag coefficient curve
Q.8
Our designed Mach number is 0.Find the required area ratio for the design. Assume isentropic relation is valid.
  • a) 1.038
  • b) 3.45
  • c) 5.64
  • d) 0.12
Q.9
____________ is the most common type of boundary layer diverter used for supersonic applications.
  • a) Channel diverter
  • b) Empennage
  • c) Aileron
  • d) Elevator
Q.10
Following diagram represents __________
Questionaircraft-design-questions-answers10.jpg
  • a) cd nozzle
  • b) convergent nozzle
  • c) divergent nozzle
  • d) constant area nozzle
Q.11
At exhaust of nozzle temperature isand density of the flow is 1.kg/mIf back pressure is 1 bar then, nozzle is ______________
  • a) nozzle can be under or over expanded
  • b) under expansion
  • c) over expanded
  • d) design condition
0 h : 0 m : 1 s