Abstract:
The probe decelerates a portion of the supersonic free stream into the subsonic range within a distributed compression fan. Stagnation pressure is sampled in the region of subsonic flow using a pitot tube. Pressure recovery has been measured over the Mach number range 1.5 to 2.5, a typical value being 0.999 at a Mach number of 1.88. The probe is usefully insensitive to misalignment with the free stream and pressure tappings in the compression surface allow it to be used also as a flow-direction sensor.
