A typical liquid fueled liquid oxygen-kerosene rocket engine is shown schematically to the right. The exit velocity of the gasses at Point B are primarily a function of the temperature at Point A. Empirical data for the test engine is provided in the table.
Create a single, professional MS Word document as a solution for this project and e-mail this document as an attachment to mheinen_1@msn.com.
Use the following format for your file:
LastName_FirstInitial-RocketLab
Example: HeinenM-RocketLab.docx
Include all calculations, data, graphs, and include explicit answers.