NASA Glenn Research Center 10- by 10-Foot Supersonic Wind Tunnel Air Heater Capability and Characterization Plans

The NASA Glenn Research Center 10- by 10-Foot Supersonic Wind Tunnel, capable of generating Mach 2.0 to 3.5 flow through the test section, is the largest high-speed propulsion wind tunnel within NASA. This facility has historically had the ability to raise the total temperature of the test section to reach flight-match total temperatures between Mach 2.0 and 3.1 using a natural-gas-supplied tunnel air heater ahead of the test section. Test section characterization efforts began in 1964 with the original 'Hot' calibration and the most recent characterization test entry to use the tunnel air heater was in 1999. To enable this capability once again, a reactivation of the heater systems and a characterization of the test section flow field and gas composition are being planned and pursued.