The accurate prediction of surface heating loads on atmospheric entry vehicles is crucial in the design of thermal protection systems (TPS) and in improving our understanding of the surface response, such as ablation, surface kinetics, and recession. The use of an immersed boundary method (IBM) solver provides a distinct advantage in the study of coupled fluid ablation interaction (FAI) problems due to the use of non-conformal grids allowing for straightforward modelling of surface recession effects. However, one of the main drawbacks of Cartesian IBM codes is the lack of shock-alignment and wall alignment for resolving the boundary layer which results in significant reconstruction errors of surface temperature gradients and in turn, heat loads for blunt body configurations. The work presented here investigates the formulation of a new sharp IBM solver employing a ghost-cell method to accurately capture the surface heat flux while avoiding prohibitively small grid spacing near the wall.
|Number of pages||16|
|State||Published - Jan 11 2021|
|Event||AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online|
Duration: Jan 11 2021 → Jan 15 2021
|Conference||AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021|
|Period||1/11/21 → 1/15/21|
Bibliographical noteFunding Information:
The authors would like to recognize and show appreciation for the financial support provided by NASA Kentucky EPSCoR RA Award no. 80NSSC19M0144 with E. Stern as the technical monitor and NASA EPSCoR R3 Award no. 80NSSC19M0084 with M. Barnhardt as the technical monitor. The authors would also like to thank the collaborators from NASA Ames Research Center, NASA Langley Research Center, and the NASA Johnson Space Center.
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
ASJC Scopus subject areas
- Aerospace Engineering