Downwash and Induced Drag MCQ

Test your knowledge with important Downwash and Induced Drag MCQ and their applications. These MCQs are beneficial for competitive exams too. Explore 30+ more Downwash and Induced Drag MCQs on Bissoy. Bissoy App

• Is lift is produced by the changing direction of the flow?
  ক

  False

  খ

  True
• Is lift and drag are the total aerodynamic force acting the body?
  ক

  True

  খ

  False
• Is induced drag is related to the amount of induced downwash?
  ক

  True

  খ

  False
• Is a higher aspect ratio flat plates has a higher lift?
  ক

  True

  খ

  False
• Is induced drag produce lift?
  ক

  True

  খ

  False
• Is wing tips vortices produce the down wash?
  ক

  True

  খ

  False
• Is vortex lines leading from the wing tips?
  ক

  False

  খ

  True
• Is air pressure on the top of the wing is lower than the pressure below the wing?
  ক

  True

  খ

  False
• Is Newton’s third law of motion is an application for lift on airfoil?
  ক

  False

  খ

  True
• Is down wash is change in direction of lift?
  ক

  True

  খ

  False
• Identify the source which does not cause drag on a finite wing.
  ক

  Skin – friction

  খ

  Flow separation

  গ

  Trailing vortices

  ঘ

  Power provide by aircraft engine
• The trailing vortex increases the requirement of power by the aircraft engine.
  ক

  False

  খ

  True
• For an inviscid, incompressible flow over finite wings, D’Alembert’s paradox occurs.
  ক

  True

  খ

  False
• Select the incorrect statement for a flow over wings.
  ক

  Induced drag comes from pressure- drag

  খ

  Pressure imbalance makes D’Alembert’s paradox does not occur

  গ

  3D flow over wings cause induced drag

  ঘ

  Induced drag is a ‘type’ of pressure- drag
• Which is the correct statement with regards to the flow over a finite wing?
  ক

  Local lift is vertical

  খ

  Downward velocity increases lift

  গ

  Local lift is inclined to vertical by induced angle of attack

  ঘ

  Free-stream velocity causes all the drag
• Induced drag is generated by a component of lift for a finite wing.
  ক

  True

  খ

  False
• For a finite wing, the local airfoil section sees the angle of attack which is called as ____
  ক

  Downwash angle

  খ

  Induced angle of attack

  গ

  Relative angle of attack

  ঘ

  Effective angle of attack
• For a finite wing, the local relative wind differs by the free-stream velocity by some angle. This angle is called as ____
  ক

  Angle of attack

  খ

  Twist angle

  গ

  Relative angle of attack

  ঘ

  Induced angle of attack
• The angle between the chord line and the direction of free-stream velocity is called the angle of attack.
  ক

  True for airfoil only

  খ

  True for wing only

  গ

  True for airfoil and partially true for wings

  ঘ

  False
• The downward velocity induced by the trailing vortex in the vicinity of the wing-tips is called as _____
  ক

  Downwash

  খ

  Local relative velocity

  গ

  Effective velocity

  ঘ

  Wing velocity
• The trailing vortex is formed at each wing-tip as there is a circulatory motion established by the____
  ক

  Leaking flow at the wing- tips

  খ

  Flowing wind

  গ

  Viscosity

  ঘ

  Air tornadoes
• Which of the following is incorrect for a finite wing?
  ক

  Streamlines on the top surface bend towards the root

  খ

  Span-wise flow at the bottom surface is towards the tip

  গ

  Higher pressure region exists at the top surface

  ঘ

  Streamlines on the bottom surface bend towards the tip
• The span-wise component of flow over the top surface of the wing flows______
  ক

  From wing-tip to root

  খ

  From root to wing-tip

  গ

  Along the free-stream direction

  ঘ

  Perpendicular to the wing upwards
• The 3D flow characteristic attributed to the wings is a by-product of_____
  ক

  Pressure imbalance over top and bottom surfaces of the wing

  খ

  Pressure imbalance between leading and trailing edge of the airfoil

  গ

  Thickness of the wing

  ঘ

  Extra lift produced
• Which is the incorrect statement with regards to the flow over an airfoil and a wing?
  ক

  Flow over airfoil is 2D

  খ

  Flow over wing is 3D

  গ

  Airfoils have a component of flow along span

  ঘ

  Wings have a component of flow along span
• The airfoil and the wing behave exactly the same way in terms of aerodynamic properties.
  ক

  True

  খ

  False
• The airfoil data can also be called as_____
  ক

  Finite wing data

  খ

  Wing data

  গ

  Flight data

  ঘ

  Infinite wing data