10/13
Updated specifications:
- Contraction ratio issue solved. Now have chosen maximum acceptable value of 10, and a current value of 9.55
- Chamber diameter is 3.5 in, which is the space that the injector needs
- Throat diameter of 1.1326 in
- Mass flow is 1.2 kg
- Exit pressure of 97329.7095 Pa
- 30 deg contraction and 15 deg expansion angles
- L* is 63-64 with a chamber length of 6 in
To do:
- Thermal analysis
- CAD update
- Graphite and phenolic erosion modeling
References:
https://ocw-mit-edu.ezproxyberklee.flo.org/courses/16-512-rocket-propulsion-fall-2005/resources/lecture_3/ (Exit pressure)
https://www.eucass.eu/doi/EUCASS2017-474.pdf (L*, contraction ratio)
https://ntrs.nasa.gov/api/citations/19710019929/downloads/19710019929.pdf (angles, general)