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Optimum Expansion Ratio Calculation by onur is a document available to read on EtoBox.
This document calculates the optimum expansion ratio and nozzle exit diameter for a rocket motor operating at 64 atmospheres chamber pressure and expanding to ambient air conditions. It shows the steps to simplify the optimum expansion ratio equation by pre-calculating terms involving k, which is given as 1.15. Plugging the pressure ratio of 0.0156 and these pre-calculated terms into the simplified equation yields an optimum expansion ratio of 9.37. Given the throat diameter of 10mm, the nozzle exit diamete
- Author
- onur
- Language
- EN