Abstract
The Mach number across the exit plane in the inviscid core of scarfed supersonic nozzles was measured using pitot probes. By capitalizing on existing hardware from an obsolete wind tunnel, the cost and time required for tunnel modifications were minimized. Experiments for estimating uncertainties in Mach number due to pitot pressure measurement error, instrumentation error and probe position error were used to establish the extent to which the survey data can be used for validation of compressible fluid dynamics codes. Surveys with pitot probes placed at an angle to the nozzle centerline allowed the flow angle near the edge of the inviscid flow to be estimated. Initial CFD calculations predict the Mach number in the inviscid core to within ± 10%, but they do not capture all of the subtle flow features observed in Schlieren photographs and pitot surveys.
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