Global surface temperature/heat transfer measurements using infrared imagingA series of studies were conducted to evaluate the use of scanning radiometric infrared imaging systems for providing global surface temperature/heat transfer measurements in support of hypersonic wind tunnel testing. The in situ precision of the technique with narrow temperature span setting over the temperature range of 20 to 200 C was investigated. The precision of the technique over wider temperature span settings was also determined. The accuracy of technique for providing aerodynamic heating rates was investigated by performing measurements on a 10.2-centimeter hemisphere model in the Langley 31-inch Mach 10 tunnel, and comparing the results with theoretical predictions. Data from tests conducted on a generic orbiter model in this tunnel are also presented.
Document ID
19920074163
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Daryabeigi, Kamran (NASA Langley Research Center Hampton, VA, United States)