Radiative transmission and absorption within the ablative heat shield of hypersonic vehicles

Alexandre Martin, Marco Panesi

Research output: Chapter in Book/Report/Conference proceedingConference contribution


The P1 approximation to the radiative transfer equation is coupled to a material response code in order to model ablative materials. These types of materials are used as thermal protection systems for atmospheric entry vehicles. Several test cases are presented to verify the implementation and to validate the approach. Representative conditions – mimicking an arc-jet, a radiant heating facility, and a re-entry trajectory – are used to demonstrate the validity of the coupled model. The code is then used to replicate an experiment that studies the effects of the wavelength on the thermal response of charring ablators. Two lasers are used to deliver the heat pulse. The first laser, at a wavelength of 1.07 μm, deposits the energy within the material, as opposed to the 10.6 μm laser, which mostly does it on the surface. The numerical results verify the findings of the experiment, thus confirming the importance of spectrally resolving the radiative heat flux within charring ablators.

Original languageEnglish (US)
Title of host publicationAIAA AVIATION 2020 FORUM
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105982
StatePublished - 2020
EventAIAA AVIATION 2020 FORUM - Virtual, Online
Duration: Jun 15 2020Jun 19 2020

Publication series

Volume1 PartF


CityVirtual, Online

ASJC Scopus subject areas

  • Nuclear Energy and Engineering
  • Aerospace Engineering
  • Energy Engineering and Power Technology


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