For air flow over a flat plate, velocity (U) and boundary layer thickness (δ) can be expressed respectively, asuu∞=32yδ−12(yδ)3; δ=4.64x√RexIf the free stream velocity is 2 m/s and air has kinematic viscosity of 1.5×10−5m2/s and density of 1.23 kg/m3, the wall shear stress at x = 1 m, is

For air flow over a flat plate, velocity (U) and boundary layer thickn

1.	For air flow over a flat plate, velocity (U) and boundary layer thickness (δ) can be expressed respectively, asuu∞=32yδ−12(yδ)3; δ=4.64x√RexIf the free stream velocity is 2 m/s and air has kinematic viscosity of 1.5×10−5m2/s and density of 1.23 kg/m3, the wall shear stress at x = 1 m, is
Answer» For air flow over a flat plate, velocity (U) and boundary layer thickness ( $δ$ ) can be expressed respectively, as $\frac{u}{u_{\infty}} = \frac{3}{2} \frac{y}{δ} - \frac{1}{2} {(\frac{y}{δ})}^{3};$ $δ = \frac{4.64 x}{\sqrt{R e_{x}}}$ If the free stream velocity is 2 m/s and air has kinematic viscosity of 1.5 $\times 10^{- 5} m^{2} / s$ and density of 1.23 kg/ $m^{3}$ , the wall shear stress at x = 1 m, is

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