Performance Calculations for a Boundary-Layer-Ingesting Fan Stage from Sparse Measurements

A test of the Boundary Layer Ingesting Inlet/Distortion Tolerant Fan was completed in NASA Glenn’s 8by 6-Foot Supersonic Wind Tunnel. Inlet and fan performance were measured by surveys using a set of rotating rake arrays upstream and downstream of the fan stage. Surveys were conducted along the 100% speed line as well as a constant exit corrected flow line passing through the aerodynamic design point. These surveys represented only a small fraction of the data collected during the test. For other operating points, data was recorded as “snapshots” without rotating the rakes which resulted in a sparser set of recorded data. This paper will discuss an approach to the analysis of these additional, lower-measurement-density data points to expand our coverage of the fan map. Several techniques will be used to enhance snapshot data and compare with survey data to assess the quality of the approach.