13-1/2 inch supersonic wind tunnel

Channel 2 utilizes an axisymmetric nozzle block mounted on the centerbody model support tube to obtain the desired external flow Mach number in the free-jet test section. Both the model air and the simulated supersonic external flow are supplied from the facility air storage system.  The model flow is ducted through the model support tube and the external flow is then drawn from a stagnation tank upstream of the nozzle block (a partial drawing of this tunnel is shown above).  The air ejectors downstream from the test section provide additional motive power to the external flow. Various Mach numbers (nominally 1.5, 2, 2.5, 3, and 4) are available by changing the nozzle block on the five-inch diameter model support tube.