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UID:0-353@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20190121T163000

DTEND;TZID=Asia/Jerusalem:20190121T173000

DTSTAMP:20230527T135401Z

URL:https://aerospace.technion.ac.il/events/unsteady-supersonic-flow-over-
 a-spiked-blunt-body/

SUMMARY:Unsteady Supersonic Flow over a Spiked Blunt Body
DESCRIPTION:Lecturer:Devabrata Sahoo\n Faculty:Department of Aerospace Engi
 neering\n Institute:Technion – Israel Institute of Technology\n Location
 :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra
 ct: \n Details: \n Blunt nose shapes such as flat-face\, hemisphere and el
 lipse are of supreme interest among the bodies moving at supersonic speeds
  due to the need for housing payloads\, radar or infrared seekers. This bl
 untness in the nose shape leads to high drag. One common solution for drag
  reduction is the use of a spike\, a slender rod mounted at the stagnation
  point. Unfortunately\, past studies have reported various types of unstea
 diness associated with mounted spikes. These oscillations could be detrime
 ntal to the purpose of the spike\, flow stability and the vehicle structur
 e itself. The main motivation for the present study is to gain a better un
 derstanding of the mechanism involved behind this flow unsteadiness in ord
 er to control and alleviate it.\nIn the present research\, three different
  forebody shapes (flat-face\, hemispherical and elliptical) mounted with a
  sharp tip spike are considered. First\, parametric studies have been carr
 ied out to investigate the sensitiveness of the spike and forebody geometr
 y on the drag reduction as well as flow unsteadiness. Then\, the flow unst
 eadiness arising over these configurations are captured and differentiated
 . The mechanism behind the shock related unsteadiness has been proposed qu
 alitatively using time-resolved high-speed shadowgraphs and explained quan
 titatively using unsteady pressure measurements along with the data based 
 modal decomposition methods and numerical simulations. Proper Orthogonal D
 ecomposition (POD) and Dynamic Mode Decomposition (DMD) methods have been 
 used to extract and study the dominant spatio-temporal modes. Finally\, on
 e example of unsteadiness alleviation has been demonstrated.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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