Abstract The high-temperature shock layer around re-entry vehicles strongly emits radiation through atomic lines and molecular bands. Radiative heat transfer strongly affects boundary layer flow and heat transfer. A novel spectral model based on k-distribution is implemented and coupled with a hypersonic flow solver in OpenFOAM to simulate heat transfer over a Martian entry vehicle. The Navier-Stokes equations with finite rate chemistry are used to model hypersonic chemically reacting flows. The convective terms in the governing equations are treated with various flux schemes (HLL, AUSM+, Kurganov, and Tadmor). The non-gray radiative properties of shock layer gases were modeled with the Emission-weighted Full Spectrum k-distribution (EFSK) method. The Radiative Transfer Equation (RTE) is solved with the P1 radiative solver to calculate the wall heat flux and radiative heat source term. At a high Mach number, the radiative heat flux is dominant compared to the convective heat flux. The numerical results for Mach number 26 are compared with published data and are found to be in good agreement. All the flux schemes provided results in close agreement, with minor differences, especially near the wall for the AUSM+ flux scheme.
Graphical abstract In this study, we developed and implemented a novel spectral model with a hypersonic reacting flow solver to model the flows around a re-entry vehicle in the Martian atmosphere. The Navier-Stokes equations with finite rate chemistry are used to model the chemically reacting flow. Non-gray shock layer gas (CO) properties have been modeled with the Emission-weighted Full Spectrum k-distribution (EFSK) method along with P1 radiative solver to calculate the wall heat flux and radiative heat source term. The flow field around the spacecraft at different Mach numbers was compared for various flux schemes, showing overall very good agreement. For higher temperature and larger entry speed, the radiative heat transfer are more dominant than the convective heat transfer. Display Omitted
Highlights Numerical analysis of hypersonic reacting flows with heat transfer around a re-entry vehicle in the Martian atmosphere. Development and implementation of a novel spectral model to calculate the radiative properties of shock layer gases. Flow-field around the spacecraft at different Ma was compared for various flux schemes, showing overall very good agreement. The shock layer's radiative cooling minimizes the shock stand-off distance and the convective heat load on the spacecraft's wall. For higher temperature and larger entry speed, the radiative heat transfer is more dominant than the convective heat transfer.
Flow and radiation modeling over a Martian entry vehicle
Acta Astronautica ; 205 ; 172-184
2023-01-22
13 pages
Article (Journal)
Electronic Resource
English
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