- #1
Emzielou83
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1. Investigate and apply equations of stae; speed of sound; continuity; bernoulli for incompressible inviscid flow; shear forces and stresses; laminar flow; flow in boundary layer link to shear forces and viscosity- continuity equation
2.
3. I have answered 90% of the question. What I don't get is the last bit - flow in boundary layer link to shear forces and viscosity- continuity equation.
I understand continuity is Mass can neither be created nor destroyed. and the formula for steady flow is ρ1A1V1= ρ2A2V2 . I understand boundary layer is the point at which no dragging effect occurs.
I also understand that viscosity effects the flow over the wing of an aircraft but surely this is the same as laminar and turbulant flow??
I don't understand the link between viscosity and continuity.
Can anyone help please??
2.
3. I have answered 90% of the question. What I don't get is the last bit - flow in boundary layer link to shear forces and viscosity- continuity equation.
I understand continuity is Mass can neither be created nor destroyed. and the formula for steady flow is ρ1A1V1= ρ2A2V2 . I understand boundary layer is the point at which no dragging effect occurs.
I also understand that viscosity effects the flow over the wing of an aircraft but surely this is the same as laminar and turbulant flow??
I don't understand the link between viscosity and continuity.
Can anyone help please??