Isentropic Compressible Flow Calculator

Description

This program takes a ratio of specific heats and a Mach number as input and outputs pressure, temperature, density, and area ratios according to these formulae (specifically formulae 6,7,8,9):

https://www.grc.nasa.gov/www/k-12/VirtualAero/BottleRocket/airplane/isentrop.html

If you want to use these variables outside the program, it may be useful to know that:
Mach is saved in variable M
Gamma/ratio of specific heats is saved in variable G
P/P_0 is saved in variable P
T/T_0 is saved in variable T
Rho/Rho_0 is saved in variable R
A/A* is saved in variable A

This program can NOT solve for Mach given these ratios! I do want to implement this; however, it is somewhat difficult especially for the area ratio, where there is a subsonic and supersonic solution for any given area ratio.

This program has been tested on a TI-84 Plus CE on OS 5.3.0, with the specific combination of Mach and gamma shown in screenshots. The output agrees with online aerodynamics calculators, so I assume the formulae are totally correct; however, I take no responsibility for any issues you may have with this.