Effect of number of probes and their orientation on the calculation of several compressor face distortion descriptors
Frederick Stoll, Jeffrey W. Tremback, Henry H. Arnaiz, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Hugh L. Dryden Flight Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979 - Technology & Engineering - 39 pages
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320 total pressure 320-probe array 40 Angular location 40 percent 40 probes 64 rakes average compressor face boundary layer centerbody support strut circumferential distortion descriptor compression mode COMPRESSOR FACE DISTORTION compressor face Ring compressor face total corrected engine airflow described in reference distortion descriptor table Dryden Flight Research Effect of Number effects of probe Eight rakes eight-rake/40-probe configuration error of distortion face total pressure fewer probes five distortion descriptors Flight Research Center Henry H Inlet plane inlet throat location of centerbody location of rake mixed-compression inlet NASA Number of probes Number of rakes percent 40 plane of symmetry Pressure maps probe number probes and rakes r a IDC Rake 1 Rake rake assembly rakes 32 rakes for three shock waves shown in figure Solid symbols denote strut wake support strut upstream three test conditions total pressure measurements Tremback upstream of compressor Variation in error WIND TUNNEL MODEL YF-12 airplane