Connected-pipe experiment and analysis for ducted rocket

The experiment system composing, design method of test motor, and experiment method are demonstrated. According to acquired data such as static temperature, static pressure and mass flow rate, analysis methods are put forward for the combustion efficiency, specific impulse efficiency. Without regard to the error during thmodynamic calculation, these parameters error are analyzed according to the current experiment system precision. It shows that the total pressure relative error is fairly higher with reduction from static pressure, static temperature and mass flow rate. This parameter should be tested directly. The relative errors of combustion efficiency, thrust gain specific impulse and bench force specific impulse are about ± 3.6%. The main error sources are air mass flow rate, static pressure and bench force. Their accuracy should be controlled restrictively in order to reduce test errors. This paper provides the helpful references for ducted rocket experiment.