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 =0 .<br>The given values are for Re<sub>c</sub>.
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 Re<sub>c</sub>=40000 and chord length is 1m, is _____
The constant which is present while establishing a relationship for C<sub>f</sub> and Re<sub>c</sub> for a laminar flow is_____
The coefficient of skin-friction drag coefficient C<sub>f</sub>, 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 Re<sub>x</sub> is . Which is____
For a Reynolds number Re<sub>c</sub>=9 10<sup>4</sup> 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_____