Heat Flux Predictions for High Speed Flows with an Immersed Boundary Method

Joel A. McQuaid, Aleksander L. Zibitsker, Alexandre Martin, Christoph Brehm

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

7 Scopus citations

Abstract

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 stationary grids which allows for straightforward modeling of surface recession effects. However, one of the main drawbacks of Cartesian IBM solvers is the lack of shock-aligned and wall-aligned grids for resolving the boundary layer which results in significant reconstruction errors of surface temperature gradients heat loads, particularly for blunt body configurations. The work presented here investigates the formulation of a body-conformal near body solver (NBS) which has been coupled to a sharp IBM solver to accurately capture the surface heat flux while avoiding prohibitively small grid spacings near the wall. The newly developed NBS-IBM solver has been formulated to handle both perfect gas and chemically-reacting flows so as to be applicable to a wide range of high-enthalpy environments where FAI problems are actively investigated.

Original languageEnglish
Title of host publicationAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
DOIs
StatePublished - 2021
EventAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021 - Virtual, Online
Duration: Aug 2 2021Aug 6 2021

Publication series

NameAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021

Conference

ConferenceAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
CityVirtual, Online
Period8/2/218/6/21

Bibliographical note

Funding 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 like to thank the collaborators from NASA Ames Research Center, NASA Langley Research Center, and the NASA Johnson Space Center. The funding support provided by the DoD HPC Modernization Program under contract FA700-19-2-0002 with Dr. Russ Cummings (Director of Hypersonic Vehicle Simulation Institute (HVSI)) as program manager is also gratefully acknowledged.

Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

ASJC Scopus subject areas

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

Fingerprint

Dive into the research topics of 'Heat Flux Predictions for High Speed Flows with an Immersed Boundary Method'. Together they form a unique fingerprint.

Cite this