The overall setup of the nominal Mach 1.6 tunnel.  This experiment demonstrates some basic concepts of supersonic flow.

A back view of  the wind tunnel.

A picture of the intake filter/silencer and all the pressure gauges of the wind tunnel.  

A picture of the test section.  Impact and static pressure probes are employed to monitor velocities in the tunnel at various stations along the flow and Schlieren system is used for examination of shock waves from objects placed in the test section.

A close-up of the test section