‘Implementing Digital Temperature Compensation (DTC) Pressure Scanners in a Supersonic Wind Tunnel’

摘要

This paper discusses the implementation of Digital Temperature Compensation (DTC) Pressure Scannertechnology in the 8x6 Foot Supersonic Wind Tunnel at the NASA Glenn Research Center. This tunnelis an atmospheric, continuous-flow propulsion wind tunnel that operates at speeds from Mach 0.4 to 2.0with corresponding total temperatures of 97o F (36o C) to 195o F (91o C). The scanners can only operateat temperatures up to 176o F (80o C). Therefore, a cooling system was fabricated to house the scannersand protect them from the wind tunnel’s high temperatures. The scanners were initially deployed for asupersonic model test and a Skin Friction Test. The pressure scanners were housed near a scale modelof a supersonic aircraft inlet within 10 ft (3.05 m) of the static and total pressure taps to reduce pressuresettling time. The Skin Friction Test addressed the same concerns, but the scanners were mounted ontop of the test section near the test plate. The digital temperature compensation technique used for theElectronically Scanned Pressure (ESP) scanners significantly improved accuracy and reduced thefrequency of on-line calibration.