Investigation of Total Momentum Ratio
Faculty Mentor Name
Daniel White
Format Preference
Poster
Abstract
The goal of this project is to analyze the effect of total momentum ratio (TMR) on combustion performance for a pintle type injector. TMR is a parameter that can be used to characterize combustion stability and the kinematics of propellant combinations. Analyzing the TMR will help in the comprehension of how the engine is combusting propellant and if it is combustion as designed. Being able to study the effect of changing TMR will help understand if industry standard “rules of thumb” apply to our engine. Currently, a concern is that the engine is not mixing and combusting propellant efficiently enough to meet flight profile parameters. The goal set by the Mountain Spirit program dictates the engine will produce 1759lbf for 20 seconds of burn duration to get the rocket to 150,000ft. To meet these requirements, there needs to be a more comprehensive study into propellant mixing and combustion performance.
Investigation of Total Momentum Ratio
The goal of this project is to analyze the effect of total momentum ratio (TMR) on combustion performance for a pintle type injector. TMR is a parameter that can be used to characterize combustion stability and the kinematics of propellant combinations. Analyzing the TMR will help in the comprehension of how the engine is combusting propellant and if it is combustion as designed. Being able to study the effect of changing TMR will help understand if industry standard “rules of thumb” apply to our engine. Currently, a concern is that the engine is not mixing and combusting propellant efficiently enough to meet flight profile parameters. The goal set by the Mountain Spirit program dictates the engine will produce 1759lbf for 20 seconds of burn duration to get the rocket to 150,000ft. To meet these requirements, there needs to be a more comprehensive study into propellant mixing and combustion performance.