An oblique shock is inclined at an angle of 35 degrees to the upstream flow of

velocity $517.56 \mathrm{~m} / \mathrm{s}$. The deflection of the flow due to this shock is 5.75 degrees and the temperature downstream is $182.46 \mathrm{~K}$. Assume the gas constant $R=287 \mathrm{~J} /(\mathrm{kg} \mathrm{K})$, specific heat ratio $\gamma=1.4,$ and specific heat at constant pressure $C_{p}=1005 \mathrm{~J} /(\mathrm{kg} \mathrm{K})$ Using conservation relations, the Mach number of the upstream flow can be

obtained as $\quad$____________ (round off to one decimal place).

An oblique shock is inclined at an angle of 35 degrees to the upstream flow of

velocity $517.56 \mathrm{~m} / \mathrm{s}$. The deflection of the flow due to this shock is 5.75 degrees and the temperature downstream is $182.46 \mathrm{~K}$. Assume the gas constant $R=287 \mathrm{~J} /(\mathrm{kg} \mathrm{K})$, specific heat ratio $\gamma=1.4,$ and specific heat at constant pressure $C_{p}=1005 \mathrm{~J} /(\mathrm{kg} \mathrm{K})$ Using conservation relations, the Mach number of the upstream flow can be

obtained as $\quad$____________ (round off to one decimal place).

The thickness of a laminar boundary layer $(\delta)$ over a flat plate is, $\frac{\delta}{x}=\frac{5.2}{\sqrt{\operatorname{Re}_{x}}},$ where $x$ is measured from the leading edge along the length of the plate. The velocity profile within the boundary layer is idealized as varying linearly with $y$. For freestream velocity of $3 \mathrm{~m} / \mathrm{s}$ and kinematic viscosity of $1.5 \times 10^{-5} \mathrm{~m}^{2} / \mathrm{s}$, the displacement thickness at $0.5 \mathrm{~m}$ from the leading edge is__________ $\mathrm{mm}$ (round

off to two decimal places).

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