The document summarizes test data from a 2-second burn of a bi-propellant thruster using 90% hydrogen peroxide and RP-1 fuel with a 6.4:1 oxidizer to fuel ratio. Key details include: - The thruster had a copper thrust chamber and fuel injector. - It generated 200 lbf of thrust during the 2-second burn. - Propellant flow rates were 330g/s for the oxidizer and 52g/s for the fuel. - Performance parameters like specific impulse and characteristic velocity were calculated from the test data and compared to theoretical values.