@inproceedings{995e0e17520b4a888910822887498c0b,
title = "Heat flux measurements in a scramjet combustor using direct write technology",
abstract = "In this experimental study, heat flux measurements were made at four locations within the isolator/combustor/nozzle region of a direct-connect gaseous hydrocarbon-fueled scramjet combustor. Combustor conditions were fixed and representative of a Mach-5 flight condition. The heat flux measurements were made using sensors deposited directly on the engine thermal barrier coating (TBC) using Direct Write Technology. Flush-wall fuel injection locations were fixed and a cavity on the body side wall provided the necessary flame holder. Overall equivalence ratios were varied from 0.6 to 1.0, but were held constant for a given run. Preliminary results show heat flux values rising with combustor equivalence ratio at all measurement locations. Heat flux values ranging from 400 to 1000 kW/m2 (35 to 88 BTU/ft2-s) were measured in the location downstream of the cavity flame holder. Heat flux values ranging from 600 to 2000 kW/m2 (53 to 176 BTU/ft2-s) were measured in the cavity flame holder location. Heat flux values ranging from 200 to 600 kW/m2 (18 to 53 BTU/ft2-s) were measured in the locations upstream of the cavity flame holder. Measured local heat flux values were consistent with area-averaged heat flux measurements over a section of the combustor.",
author = "Kennedy, \{Paul J.\} and Donbar, \{Jeffrey M.\} and Trelewicz, \{Jason R.\} and Christopher Gouldstone and Longtin, \{Jon P.\}",
year = "2011",
doi = "10.2514/6.2011-2330",
language = "English",
isbn = "9781600869426",
series = "17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011",
booktitle = "17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011",
note = "17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 ; Conference date: 11-04-2011 Through 14-04-2011",
}