2. Aerodynamics
Compressible Flow — Quiz
Test your understanding of compressible flow with 5 practice questions.
Practice Questions
Question 1
Which stagnation property remains constant across a normal shock in a perfect gas?
Question 2
For supersonic flow with Mach number $M=2.5$, what is the Mach angle $\mu$? Show your calculation.
Question 3
A normal shock wave occurs at upstream Mach number $M_{1}=2.5$ in air ($\gamma=1.4$). What is the downstream Mach number $M_{2}$? Show your calculation.
Question 4
In a converging–diverging nozzle under design conditions with exit Mach number $M_{e}=2$ and $\gamma=1.4$, what is the exit-to-throat area ratio $A_{e}/A^{*}$? Show your calculation.
Question 5
When supersonic flow encounters a concave corner, which phenomenon occurs?