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DOI
https://doi.org/10.13023/ablat.2012.50
Event Date
2-28-2012
End Date
1-3-2012 12:30 PM
Abstract
Entry of spacecraft into an atmosphere occurs at hypersonic speeds, extremely complex flow fields, with aerothermodynamic effects which can cause the surface to be subjected to extreme heating. It is therefore important to protect the vehicle and its payload using a thermal protection system (TPS). Heat shields, which are an important part of a TPS, can be of either ablative or non-ablative types. For an ablative TPS, the energy is dissipated through surface material charring and ablation, as well as releasing gasses which serve to carry energy away from the TPS and thus reduce the total heat flux into the vehicle.
Abstract and figures
Experimental Investigation of Blowing Effects on Turbulent Flow Over a Rough Surface
Entry of spacecraft into an atmosphere occurs at hypersonic speeds, extremely complex flow fields, with aerothermodynamic effects which can cause the surface to be subjected to extreme heating. It is therefore important to protect the vehicle and its payload using a thermal protection system (TPS). Heat shields, which are an important part of a TPS, can be of either ablative or non-ablative types. For an ablative TPS, the energy is dissipated through surface material charring and ablation, as well as releasing gasses which serve to carry energy away from the TPS and thus reduce the total heat flux into the vehicle.
Notes
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The complete abstract and figures are available as the additional file listed below.