Testing a fluidic temperature sensor on a subscale ramjet engine combustion chamber

Data obtained from 26 tests that used three fluidic temperature sensors to measure gas temperatures in a subscale ramjet engine combustion chamber are presented. The test variables for the combustion chamber were chamber pressure and chamber temperature. Tests were conducted using nominal chamber pressures of 35 and 70 psia and chamber total temperatures of 2500 R, 3000 R, and 3800 R. One of the sensors used various insulator materials which were magnesium oxide, Hastelloy X, and zirconium oxide. These materials varied the conduction heat losses from the sensor body to the outer case. The mass flow through a sensor was increased by a factor of three to see if improvements could be made in reducing steady state error or increasing thermal response. Lastly, one test was conducted using an ablative lined combustion chamber that provided a long duration run.