Cold Flow Test!

Looking up the nozzle of the Pyralis Cold Flow prototype

Looking up the nozzle of the Pyralis Cold Flow prototype

Today the MIT Rocket Team conducted a successful cold flow test of the Pyralis rocket engine prototype. We flowed compressed nitrogen gas at 4.1 MPa (600 psi) pressure through the engine’s nozzle and combustion chamber, generating about 220 N (50 lbs) of thrust force.

Over the next weeks,we will continue to test the Cold-Flow prototype and will use the data from these test to inform the design of the next, high-temperature version of the Pyralis Engine.

Thanks to Jimmy Letendre of MIT’s Gas Turbine Lab for providing us with a testing space.

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