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UID:0-525@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20150211T163000

DTEND;TZID=Asia/Jerusalem:20150211T173000

DTSTAMP:20230603T193223Z

URL:https://aerospace.technion.ac.il/events/film-cooling-of-a-blunt-body-i
 n-supersonic-high-enthalpy-flows/

SUMMARY:Film Cooling of a Blunt Body in Supersonic High Enthalpy Flows
DESCRIPTION:Lecturer:Segoula Uzan\n Faculty:Department of Aerospace Enginee
 ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl
 assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract:
  \n Details: \n During atmospheric re-entry at hypersonic speed or at very
  high speed flight in the atmosphere\, vehicles experience extremely high 
 thermal loads for relatively long times: the classical thermal protection 
 materials do not survive and need to be replaced by lightweight actively c
 ooled components. This work investigates experimentally film cooling of a 
 blunt body in a supersonic high enthalpy flow. The coolant\, injected in t
 he stagnation zone of the blunt body surface against the free stream\, ope
 rates as a thin\, cool\, insulating layer\, yielding a thickening of the b
 oundary layer\, thus reducing the temperature gradient of the surface. The
  experiments were performed in the Aerothermodynamics Laboratory in the Te
 chnion\, where a plasma arc tunnel enables simulation of high enthalpy flo
 ws. Two models (with and without injection) were exposed to a Mach 2.2 fre
 estream with a total enthalpy of 1.7 MJ/kg. Nitrogen and helium were used 
 as coolant gases. A parametric study shows the influence of coolant physic
 al properties and mass flow rate on the characteristics of the flow surrou
 nding the model and on the resulting temperature reduction at different lo
 cations on the test model.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20141026T010000

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