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/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)