The picture shows the top hatch (looking up and downstream from the test section) in the 20 Inch Supersonic Wind Tunnel Test Section located at Langley Research Center. This supersonic facility is capable of Mach Numbers from 1.4 to 5.0 and total pressures from less than 1 PSI to 130 PSI with a mass flow limit of 280 lb./sec. The tunnel is located in Building 1247D (1D East Reid Street) Room 107 at NASA Langley Research Center. The tunnel operates in a blowdown mode, and is designed for string mounted models with platforms less than 100 square inches in area. The picture shows the optical fused quartz window and the diagonal probe both mounted in the removable top hatch. The window provides additional optical access from above the test section in addition to the two test section side windows allowing any optical measurement technique to be used. Standard force pressure and temperature measurements can be also made in this facility as well. The tunnel has a model injection capability from a plenum underneath the test section with an injection time of 2 seconds from the time the model enters the shear layer to the center of the test section.
