Development of a Probe for Particle Collection in High-Temperature, Supersonic Flow: Conceptual and Detailed Design

An intrusive technique for the collection of the condensed combustion products in the proximity of the rocket nozzle is proposed. In particular, a supersonic probe able to withstand the harsh environment of a plume was sized to handle a progressive deceleration and cool down of the exhaust gas, preventing from liquid particle breakup. The task was achieved by diluting the swallowed flow with a cold inert gas and quenching the suspended particles using a liquid spray in a specific chamber. Preliminary tests performed in the supersonic wind tunnel at DLR confirmed the quality of the collection device.