The essential assumption of airfoil being a flat plate with a zero an – McqOptions

MCQOPTIONS

1.	The essential assumption of airfoil being a flat plate with a zero angle of attack gives accurate results always.
A.	False
B.	True
Answer» B. True

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_____