Learning Forum

[Jesús Urbina]

I am currently working on a 2D analysis for a supersonic flow (Mach= 2.13) over an airfoil. However, it is not clear to me how to define the farfield pressure.

I tried to calculate it using the following - isentropic - relation:



Total pressure: 1 atm
Static pressure: Farfield pressure at mach= 2.13 (this is the variable I want to define in the analysis)
Specific heats coefficient= 1.4

I suspect I didn't chose the right value for the Total Presure. What might be worth to check? What could have gone wrong with my calculations?

Worth to mention that I am using an absolute pressure. Hence, I defined the gauge pressure as 0 (Operating Conditions).

[Federico]

I'm not sure what is your question. If using ideal gas, you have the right approach. Plug in your numbers and solve for p. You will then enter p and M in the pressure farfield BC.

You should find p ~ 0.1 p0