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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.
Screenshots
Archive Contents
Name | Size |
---|---|
COMPFLOW/COMPFLOW.8xp | 358 bytes |
COMPFLOW/input.png | 5.3 KB |
COMPFLOW/output.png | 7.3 KB |
COMPFLOW/README.txt | 1.1 KB |
- File Size
- 13.5 KB
- Short link
- http://ceme.tech/DL2073
Metadata
- Author
- GigaG
- Uploaded
- 3 years ago
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Reviews
Nobody has reviewed this file yet.Versions
- FLOW84 Compressible Flow Calculator (published 3 years ago; 2020-11-20 22:20 UTC)
- Isentropic Compressible Flow Calculator (published 3 years ago; 2020-11-16 19:49 UTC)
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