Coupling Simulation of Thermal Response to Exhaust Gas at External Nozzle
- 1 January 2022
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Spacecraft and Rockets
- Vol. 59 (1), 260-270
- https://doi.org/10.2514/1.a35018
Abstract
This paper examines thermal response behind the high-Mach integrated control (HIMICO) experiment’s engine. In this experimental aircraft, instruments must be protected from heat load due to exhaust gas; therefore, a coupling calculation between the fluid and the wall is conducted to confirm the performance of HIMICO’s thermal protection system (TPS). First, the validity of the coupling calculation is confirmed through comparison with aerodynamic heating on a hollow cylinder. The present calculation result can reproduce the surface temperature distribution on the cylinder better than previous work has managed because we consider the turbulence effect. Second, one-dimensional heat-transfer analysis is conducted on the external nozzle, and the appropriateness of the calculation result is confirmed through comparison with the ramjet-engine experiment. Finally, a coupling calculation between the fluid and the wall is conducted to investigate the local temperature distribution. The calculation result indicates that the temperature increase easily meets design requirements and that TPS performance is sufficient.Keywords
Funding Information
- Japan Society for the Promotion of Science (JP20H05654)
This publication has 12 references indexed in Scilit:
- Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket NozzlesJournal of Spacecraft and Rockets, 2017
- Investigation of turbulence models with compressibility corrections for hypersonic boundary flowsAdvances in Mechanical Engineering, 2015
- Two-Dimensional Ablation and Thermal Response Analyses for Mars Science Laboratory Heat ShieldJournal of Spacecraft and Rockets, 2015
- Time-Adaptive, Loosely Coupled Strategy for Conjugate Heat Transfer Problems in Hypersonic FlowsJournal of Thermophysics and Heat Transfer, 2014
- Chemical Erosion of Carbon-Phenolic Rocket Nozzles with Finite-Rate Surface ChemistryJournal of Propulsion and Power, 2013
- Towards shock-stable and accurate hypersonic heating computations: A new pressure flux for AUSM-family schemesJournal of Computational Physics, 2013
- Cork: properties, capabilities and applicationsInternational Materials Reviews, 2005
- Ablation and Thermal Response Program for Spacecraft Heatshield AnalysisJournal of Spacecraft and Rockets, 1999
- Application of integral methods to ablation charring erosion - A reviewJournal of Spacecraft and Rockets, 1995
- Experimental study of shock wave interference heating on a cylindrical leading edge at Mach 6 and 8Published by American Institute of Aeronautics and Astronautics (AIAA) ,1987