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UID:0-405@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20180423T163000

DTEND;TZID=Asia/Jerusalem:20180423T173000

DTSTAMP:20230530T180425Z

URL:https://aerospace.technion.ac.il/events/performance-improvement-of-bou
 ndary-layer-ingesting-inlets-using-active-flow-control-techniques-computat
 ional-analysis/

SUMMARY:Performance Improvement of Boundary Layer Ingesting Inlets Using Ac
 tive Flow Control Techniques (Computational Analysis)
DESCRIPTION:Lecturer:Irena Rudin\n Faculty:Department of Aerospace Engineer
 ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla
 ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: 
 \n Details: \n In recent years\, revolutionary technologies of inlet desig
 n were developed in response to environmental concerns such as reduction o
 f noise and pollution. Part of these efforts are directed towards reductio
 n of overall weight and drag of air vehicles. BLI (boundary layer ingestin
 g) serpentine integrated inlets\, with high curvature are a critical compo
 nent of this design trend and very attractive for weight and drag reductio
 n. However\, they suffer of the disadvantage of thick boundary layer inges
 ted into the inlet coupled with S–shaped offset that induce losses of to
 tal pressure and flow uniformity inside the inlet.\nThe current study disp
 lays control authority over flow non-uniformity using several active flow 
 control methods\, such as suction and blowing. The analysis is performed u
 sing RANS and URANS simulations. The focus is on applying active flow–co
 ntrol method on a BLI inlet in order to restructure the flow inside the in
 let and to improve engine fan–face distortion levels. First\, a baseline
  case\, without any flow control was calculated and compared to previously
  published experimental and computational results. The results of the base
 line calculation were used to determine the flow mechanisms that character
 ize the formation of flow distortion inside the inlet. Based on these resu
 lts\, desirable positions of suction slots could be determined in various 
 combinations. However\, to achieve significant decrease in flow distortion
 \, non-neglectable mass flow was required for the suction. Therefore\, com
 binations of steady suction and steady/oscillatory blowing were examined. 
 Using this AFC approach\, a significant improvement in pressure recovery a
 nd flow uniformity was demonstrated\, at a negligible loss in the mass flo
 w rate.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20180323T030000

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