Compressible Flow

Compressible Flows Equations:
1) Isentropic relationships
2) Normal Shock Calculator for aerodynamics compressible flows
3) Gas properties, more will be added


P0=stagnation pressure, T0=stagnation temperature
Equations:
P0=P*(1+0.5(gamma-1)Mach^2)^(gamma)/(gamma-1)
T0=T*(1+0.5(gamma-1)Mach^2)

For engineering students and/or aerospace engineers; let me know how I can improve this app

The Heat Capacity ratio of the gas can be changed and few references values can be chosen

More data can be found on http://en.wikipedia.org/wiki/Heat_capacity_ratio

Disclaimer:
I have checked the equations but it is always possible to have a bug; double check the results

fonts used in the icon Crimson Text: http://aldusleaf.org/index.php