General Design Specifications:

• Butanol & Liquid Oxygen

• Combustion Pressure : 1380 kPa

• Combustion Temperature: 3000 °C

• Thrust 2.22 kN

• Specific Impulse (sea level) : 255 s

• Burn Time Capability: 20 Seconds

• Regenerative & Film Cooling Approach

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This project is currently active, and being pursued rigorously by myself & the Oregon Tech Rocketry & Aerospace club. This was my Senior Project. The specifications for this engine are suitable for competing in the Spaceport America Cup. 

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My contributions include

• Combustion Chamber Design & Analysis

  • You can see how I designed this on the OTRA blog here​

  • Material selection excel sheet available for viewing here

• Nozzle Geometry Design​ & Analysis

• Cooling Design & Analysis

  • I did the design and analysis of the regenerative cooling system

• Combustion Dynamics Analysis

  • Mode calculations & geometry considerations.​

• Manufacturing​ 

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