For the same angle of attack and chord length, the boundary layer is – McqOptions

MCQOPTIONS

1.	For the same angle of attack and chord length, the boundary layer is thicker in_____
A.	Turbulent flows
B.	Laminar flows
C.	Will be equal in both the flows
D.	Depends on the velocity of flow
Answer» B. Laminar flows

Discussion

No Comment Found

Related MCQs

All bodies have skin-friction contribution more than that from the pressure drag.
Which of the following gives a better approximate distribution of drag over thin airfoils?The given percentages are for skin- friction drag and pressure drag respectively.
For the boundary layer profile given below, select the regions which best represents where the transition in flow is taking place and mark the leading edge (respectively).
The phenomena best represented by the profile given in the following figure is_____
When the free-stream velocity is made one-third, the transition point moves downstream.The given statement is true or false?
The transition point for a flow can be found using____
For a real flow over an airfoil, with Reynolds number in the laminar region as it starts, select the incorrect choice.
The skin-friction coefficient for turbulent flow Cf is proportional to Rec. The proportionality constant is_____
A given flow can be laminar all over an airfoil in a real case. Select the correct statement for the assumption given above.
The boundary layer thickness for turbulent flow at a distance x with Reynolds number Rex is δ. Which is____