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
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| Downloads: 5 | ||||
| Updated At: 2024-04-22 15:09:29 | ||||
| Publisher: aero-calculator | ||||
| Operating System: Android | ||||
| License Type: Free |