Abstract
An uncertainty analysis procedure was developed for the AFRL/RZAS Supersonic Combustion Research Laboratory to characterize the uncertainty associated with direct-connect-combustor performance parameters such as combustion efficiency and stream thrust. The uncertainty calculation uses a comprehensive approach (based on AGARD AR-223, ASME PTC 19.2-1998, and AIAA S-071A-1999) that includes the calibration standard accuracy, individual sensor calibrations, fundamental sensor measurements, intermediate performance variable determination, influence coefficients, and equilibrium code calculations. Knowledge of these uncertainties is critical in applying quantitative direct-connect test results in a meaningful manner in support of the combustion testing that is performed as part of our in-house development programs in hypersonic airbreathing engines. This information also guides investment strategies aimed at improving the overall confidence associated with reported engine performance values. This paper provides details of the uncertainty analysis procedure and results from a recent combustion test. Areas are identified where improved instrumentation will reduce the uncertainty associated with key performance measures. NOMENCLATURE
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