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      Impact of Non-Tangent-Slab Radiative Transport on Flowfield–Radiation Coupling

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          For coupled flowfield–radiation simulations, required for Earth entry at velocities greater than 10    km / s , tangent-slab radiative transport is shown to sufficiently model the divergence of the radiative flux (this term couples the radiative energy to the flowfield energy equations). However, as shown in previous studies, the tangent-slab approximation does not sufficiently model the radiative flux reaching the surface (i.e., the radiative heating). These conclusions are reached through the development of a detailed ray-tracing approach capable of computing both the divergence of the radiative flux and the radiative heating. This approach is orders of magnitude more computationally expensive than the tangent-slab approximation. The ability of the tangent-slab approach to accurately model the divergence of the radiative flux, but not the radiative heating, is shown to be the result of a cancellation of errors during the angular integration. The current work shows that combining the tangent-slab approximation for the divergence of the radiative flux with the ray-tracing approach for the radiative heating (as a final step) provides sufficiently accurate results (radiative heating values within 1%), in an efficient manner, for coupled flowfield–radiation problems.

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          Influence of Radiative Absorption on Non-Boltzmann Modeling for Mars Entry

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            Influence of Ablation on Radiative Heating for Earth Entry

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              Radiative Heating on the After-Body of Martian Entry Vehicles


                Author and article information

                Journal of Spacecraft and Rockets
                J. Spacecraft
                American Institute of Aeronautics and Astronautics
                26 February 2018
                July–August 2018
                : 55
                : 4
                : 899-913
                NASA Langley Research Center , Hampton, Virginia 23681
                Author notes

                Aerospace Engineer, Aerothermodynamics Branch; christopher.o.johnston@ 123456nasa.gov . Member AIAA.


                Aerospace Engineer, Aerothermodynamics Branch; ali.r.mazaheri@ 123456nasa.gov . Member AIAA.

                A34072 A34072
                This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0022-4650 (print) or 1533-6794 (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                Page count
                Figures: 26, Tables: 0
                Full-Length Paper

                Engineering, Physics, Mechanical engineering, Space Physics


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