Looking up the nozzle of the Pyralis Cold Flow prototype

Cold Flow Test!

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…

James and Ryan setting up the Test Stand in the Gas Turbine Lab

Cold Flow Test Setup

We’ve spent the past week putting the finishing touches on the Cold Flow test stand and engine. Yesterday, we moved the test stand into a blast chamber in MIT’s Gas Turbine Lab where we will conduct several Cold Flow tests of the Pyralis prototype next week. Thanks to Jimmy Letendre and Prof. Spakovszky for letting…