10/27
Updated specificationsUpdated 11/17:
| Specification | Value |
|---|---|
| Contraction Area Ratio | 8. |
| 73 | |
Chamber Diameter | 3.25 in ( |
| minimum) | |
| Throat Diameter | 1. |
| 1 in ( |
| minimum) |
Characteristic Length |
| 57.8 in | |
Chamber Length | 6 in |
Contraction Angle | 30 deg |
| Expansion Angle | 15 deg |
| Exit Diameter | 2. |
| 504 in | |
| Ideal Exit Pressure | 14. |
| 04 psi | |
Expansion Ratio | 5.18 |
Chamber Pressure |
| 445 psi | |
Chamber Temperature | 3023 K (stagnation) |
| Mass Flow | 1. |
| 18 kg/s | |
| Exit Mach Number | 2. |
| 7 | |
| OF Mixture Ratio | 4.15 |
| Specific Impulse | 234s |
| Average Thrust | 2600 N |
- Contraction ratio issue solved. Now have chosen maximum acceptable value of 10
- Exit pressure is 97329.71 Pa, ideal calculations, see if matches RPA
- nozzle sized 1~1.5 mm less to account for expected 0.1 mm/s erosion
- exit area also sized down to match nozzle (with slight round up)
To do:
- Thermal analysis
- Graphite and phenolic erosion modeling
- O-ring sizing
- FEA
- ThermocoupleSlides
References:
https://ocw-mit-edu.ezproxyberklee.flo.org/courses/16-512-rocket-propulsion-fall-2005/resources/lecture_3/ (Exit pressure)
...