The laminar boundary layer for a thin airfoil is maximum at_____ – McqOptions

MCQOPTIONS

1.	The laminar boundary layer for a thin airfoil is maximum at_____
A.	Leading edge
B.	Trailing edge
C.	Quarter-chord
D.	We can’t say without calculating
Answer» C. Quarter-chord

Discussion

No Comment Found

Related MCQs

Select the flow which is not laminar all over the thin airfoil at α=0°.The given values are for Rec.
The laminar boundary layer for a thin airfoil is maximum at_____
We can get the skin-friction drag coefficient for a laminar flow for a flat plate by using x as chord length in local skin- friction drag coefficient calculation.
The total skin-friction drag coefficient for laminar flow with Reynolds number at the trailing edge being Rec=40000 and chord length is 1m, is _____
The constant which is present while establishing a relationship for Cf and Rec for a laminar flow is_____
The coefficient of skin-friction drag coefficient Cf, as conventionally defined, when used gives half the value of total drag.
For finding the skin- friction drag we need to only measure shear-stress at the top or bottom surface.
The boundary layer thickness for an incompressible, laminar flow at a distance x with Reynolds number Rex is δ. Which is____
For a Reynolds number Rec=9×104 and chord length 1m, what is the laminar boundary layer thickness at the trailing edge (in cm)?
The Reynolds number for a fluid with density d, free-stream velocity V, viscosity u at a distance x from the leading edge is_____