为研究外侧面燃烧固体燃料冲压发动机燃烧室流场及燃面退移速率的特点,在Fluent平台上完成了内孔、外侧面燃烧SFRJ的燃烧室内燃烧流场的数值计算。在所涉及的工况中,计算结果表明:外侧面燃烧的SFRJ中,再附着点之前,燃面退移速率较大,来流空气质量流率150g/s,总温600 K时,最大燃面退移速率比内孔燃烧增大43.5%;再附着点之后,燃面退移速率快速减小;随着来流空气总温的减小,固体燃料末端的燃面退移速率开始沿轴向增大;随着来流空气质量流率的增大,燃面退移速率开始增大的位置不断前移,而其增大速率不断减小;因大部分区域内燃面退移速率较小,导致其平均燃面退移速率比内孔燃烧减小21.9%至40.5%;外侧面燃烧的推力比内孔燃烧的小,但比冲相差不大;补燃室及喷管表面处流场温度比内孔燃烧低500~1000 K。 In order to study the characteristics of the flow field and combustion surface backoff velocity in the combustion chamber of solid fuel ramjet, the numerical calculation of the combustion flow field in the combustion chamber with internal and external combustion SFRJ was completed on the Fluent platform. In the working conditions involved, the calculation results show that, in the SFRJ burning on the outer side, before the reattachment point, the surface burning rate is relatively large, and the mass flow rate of incoming air is 150g / s. When the total temperature is 600 K, the maximum combustion Surface rebuild rate increased 43.5% than the bore combustion; reattachment point, the combustion surface rapid decline in the rate of retreat; with the total air temperature decreases, the end of the solid fuel end of the fuel surface velocity in the axial direction Increase with the increase of the air mass flow rate of the incoming stream, the position at which the rate of return of the combustion surface began to increase continued to increase while the rate of increase continued to decrease. Because the rate of return of the combustion surface in most areas was small, Resulting in a reduction of 21.9% to 40.5% in the average burned rate compared with the internal combustion. The thrust of the external combustion is smaller than that of the internal combustion but less than that of the internal combustion. The temperature of the flow field at the combustion chamber and nozzle surface is lower than that of the internal combustion Burning low 500 ~ 1000 K.