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### Abstract

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.

### Most cited references29

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

(2014)
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• Record: found

### Influence of Ablation on Radiative Heating for Earth Entry

(2009)
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• Record: found

### Radiative Heating on the After-Body of Martian Entry Vehicles

(2015)
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### Author and article information

###### Conference
jsr
Journal of Spacecraft and Rockets
J. Spacecraft
American Institute of Aeronautics and Astronautics
0022-4650
1533-6794
26 February 2018
July–August 2018
: 55
: 4
: 899-913
###### Affiliations
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.

###### Article
A34072 A34072
10.2514/1.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
###### Categories
Full-Length Paper

Engineering, Physics, Mechanical engineering, Space Physics