A study of active-flow control in a small-scale boundary layer ingestion inlet was conducted at the NASA Langley Basic Aerodynamic Research Tunnel (BART). Forty MEMS pressure sensors, in a rake style configuration, were used to examine both the mean (DC) and high frequency (AC) components of the total pressure across the inlet/engine interface plane. The mean component was acquired and used to calculate pressure distortion. The AC component was acquired separately, at a high sampling rate, and is used to study the unsteady effects of the active-flow control. An identical total pressure rake, utilizing an Electronically Scanned Pressure (ESP) system, was also used to calculate distortion; a comparison of the results obtained using the two rakes is presented.
Comparison of Engine/Inlet Distortion Measurements with MEMS and ESP Pressure Sensors
24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference ; 2004 ; Portland, OR, United States
2004-01-01
Preprint
Keine Angabe
Englisch
A remark concerning engine-inlet distortion.
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