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本文用数值方法研究了高超声速大钝头体绕流辐射流场。采用粘性激波层控制方程和平衡化学反应气体模型。辐射部价包括连续辐射和线辐射。采用切平板辐射输运模型解决了空间推进的问题。计算结果表明：辐射传热与飞行器再入飞行速度、高度及头部半径密切相关。在计算的条件下，当再入速度小于７．６公里／秒时，辐射传热的影响可以忽略，当再入速度为１１公里／秒左右时，辐射传热可以与对流传热相比拟。当再入速度更大时，辐射传热远大于对流传热。
In this paper, numerical simulation of the flow field of hypersonic blunt body around the flow. Adopt viscous shock layer governing equation and balance chemical reaction gas model. Radiation price includes continuous radiation and linear radiation. The problem of space propulsion has been solved by using the slab radiation transport model. The calculation results show that the radiative heat transfer is closely related to the reentry flight speed, altitude and head radius of the aircraft. Under the condition of calculation, when the reentry speed is less than 7.6 km / s, the influence of radiative heat transfer can be ignored. When the reentry speed is about 11 km / s, the radiative heat transfer can be compared with the convective heat transfer. When the reentry speed is greater, radiative heat transfer is much larger than convective heat transfer.