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Total pressure recovery, ratio of total pressure at the engine face to freestream total pressure Root Mean Square level of turbulence about the average Precision index Engine corrected airflow ( 113111/sec) Number of measurements Student 't' value for 95% data inclusion Average or mean of 'n' measurements Angle-of-attack (deg) Angle-of-sideslip (deg) Standard deviation Pt2/pto RMS Turb Wac2 .. to5 a 13 ABSTRACTThe objectives of this analysis were to establish precision and bias errors for an analog-digital hybrid computer system (DYNADEC) used in the dynamic data editing phase of inlet wind tunnel testing. An uncertainty analysis was initiated to evaluate the system using inlet data from the Aeronautical Systems Center (ASC)/Arnold Engineering Development Center (AEDC) Aeropropulsion System Test Facility (ASTF) Freejet Development Program. Three test points from a subscale freejet test of the F-15 air induction system and three test points from a wind tunnel test of this same F-I5 inlet model were selected to represent a wide range of test conditions and turbulence levels. Precision errors of the 40 total pressure probes at the location of the engine face were I--2% of the 40 total pressure recovery magnitudes. Precision errors of the Pratt and Whitney 1Ca2 distortion index, the parameter used to edit the data on DYNADEC, were also investigated. These results indicated that K a2 precision errors decreased with higher turbulence levels. Static bias errors were also computed by sending known signals through the DYNADEC system and measuring the output quantity. Static bias errors were much smaller in comparison to the precision error magnitudes and were considered negligible. This analysis also provided a foundation to evaluate future data sets using this editing system. NOMENCLATUREAEDC Arnold Engineering Development Center ACP Aerodynamic interface plane ASTF Aeropropulsion Systems Test Facility IRP Inlet reference plane Ka2 Pratt and Whitney distortion index Km2 Radial distortion component of K a2 Circumferential distortion component of Ka2 Presented at
Total pressure recovery, ratio of total pressure at the engine face to freestream total pressure Root Mean Square level of turbulence about the average Precision index Engine corrected airflow ( 113111/sec) Number of measurements Student 't' value for 95% data inclusion Average or mean of 'n' measurements Angle-of-attack (deg) Angle-of-sideslip (deg) Standard deviation Pt2/pto RMS Turb Wac2 .. to5 a 13 ABSTRACTThe objectives of this analysis were to establish precision and bias errors for an analog-digital hybrid computer system (DYNADEC) used in the dynamic data editing phase of inlet wind tunnel testing. An uncertainty analysis was initiated to evaluate the system using inlet data from the Aeronautical Systems Center (ASC)/Arnold Engineering Development Center (AEDC) Aeropropulsion System Test Facility (ASTF) Freejet Development Program. Three test points from a subscale freejet test of the F-15 air induction system and three test points from a wind tunnel test of this same F-I5 inlet model were selected to represent a wide range of test conditions and turbulence levels. Precision errors of the 40 total pressure probes at the location of the engine face were I--2% of the 40 total pressure recovery magnitudes. Precision errors of the Pratt and Whitney 1Ca2 distortion index, the parameter used to edit the data on DYNADEC, were also investigated. These results indicated that K a2 precision errors decreased with higher turbulence levels. Static bias errors were also computed by sending known signals through the DYNADEC system and measuring the output quantity. Static bias errors were much smaller in comparison to the precision error magnitudes and were considered negligible. This analysis also provided a foundation to evaluate future data sets using this editing system. NOMENCLATUREAEDC Arnold Engineering Development Center ACP Aerodynamic interface plane ASTF Aeropropulsion Systems Test Facility IRP Inlet reference plane Ka2 Pratt and Whitney distortion index Km2 Radial distortion component of K a2 Circumferential distortion component of Ka2 Presented at
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