Determine, for the airflow through the frictionless and
Chapter 11, Problem 11.69(choose chapter or problem)
Determine, for the airflow through the frictionless and adiabatic converging–diverging duct of Example 11.8, the ratio of duct exit pressure to duct inlet stagnation pressure that will result in a standing normal shock at: (a) x = +0.1 m, (b) x = +0.2 m, (c) x = +0.4 m. How large is the stagnation pressure loss in each case?
Unfortunately, we don't have that question answered yet. But you can get it answered in just 5 hours by Logging in or Becoming a subscriber.
Becoming a subscriber
Or look for another answer