Compressible Flow Questions & Answers  
Please ask your questions related to Compressible Flow in this thread, I will answer them as soon as possible. To insert mathematics use LATEX. For instance, let's say we wish to insert math within a sentence such as $P$ is equal to $\rho R T$. This can be done by typing \$P\$ is equal to \$\rho R T\$. Or, if you wish to display an equation by itself out of a sentence such as: $$ \frac{P_\circ}{P}=\left( 1 + \frac{\gamma1}{2} M^2 \right)^{\gamma/(\gamma1)} $$ The latter can be accomplished by typing \$\$\frac{P_\circ}{P}=\left( 1 + \frac{\gamma1}{2} M^2 \right)^{\gamma/(\gamma1)} \$\$. You can learn more about LATEX on tug.org. If the mathematics don't show up as they should in the text above, use the Chrome browser instead of Internet Explorer.




A shear layer is a viscous flow phenomenon. Here we are solving inviscid flow. In inviscid flow, the slip line is the boundary between two flow regions.


The two flow regions have the same pressure and their velocity vectors point in the same direction. However, the temperature, density, and the magnitude of the velocity may differ.




But if $M_2=1$, then $T_2$ will have a different value than the one you computed..






In 1D (as schematized in the midterm exam Q3), it's definitely possible to have an inlet with no shock. In 2D, you could design the inlet so that the flow slows down isentropically to Mach 1 through a Prandtl Meyer compression fan. In practice this is hard to achieve because such a design would only work for one specific Mach number and lead to major losses in performance at slightly different Mach numbers. Thus, inlets generally have several shocks to allow for some variation in geometry. But this is not mentioned (or schematized) in the question statement, so you can assume the flow isentropic through the inlet here.



$\pi$ 