Abstract: During reentry process, aerodynamic shape of a capsule changes as thermal protection material ablates and recesses. It may have negative reaction on reentry performance. Studies on recession influence of Soyuz-shaped return capsule at single ballistic phase have been already carried out in a previous paper. In order to further investigate the influence of the recession, ablation models and heat mechanisms are used to calculate the material ablating of the Soyuz-shaped return capsule. Four recessed configurations were obtained at different reentry times, and the maximal recessed values of the ablation are 2.3mm, 7.8mm, 9.8mm and 12.5mm, respectively. Based on these data, numerical simulation was employed to study the effect of the recession on the Soyuz-shaped return capsule. The aerodynamic characteristic was calculated and analyzed for the initial configuration and the four different recessed configurations, and then compared with that in the previous study. The results indicate that the recessed value of the ablation increases along the trajectory. The ablation and recession reduce trim angle of attack, while the absolute value increases. They also lead to the increment of the trim lift-drag ratio and the forward movement of the longitudinal pressure center. The effect of the ablation becomes more intensive as the recession value increases. The variation of the trim angle of attack presents linear relation to the recessed value of the ablation. The present results have a qualitative agreement with those of the CEV in references, and also validate the conclusions in the previous paper.