空空导弹发动机尾流对后弹体烧蚀的数值分析

[�z�Ӆ��jQ'�*�g����~�"�ȥx�h��ږ�Ϯ��rإz�hrG��Ȭ�)^����jw�M9�]��z�)†)ޱ�駶���"http://www.film1981.com/doc/fangan/" target="_blank" class="keylink">方案研究[J]. 推进技术， 2014， 35（10）： 1310-1316.

He Xuzhao， Qin Si， Zeng Xuejun， et al. Experiment Scheme Research on Afterbody Nozzle Plume Interference on AirBreathing Hypersonic Vehicle Fly Condition[J]. Journal of Propulsion Technology， 2014， 35（10）： 1310-1316.（in Chinese）

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Abstract： Aiming at the ablation of rocket plume on airtoair missile to afterbody， the 3D flow field is simulated using CFD method， which is compared with the result of flying test， in order to analyze the common cause of ablation and investigate the influence of flying altitude and Mach number on ablation. The results show that the main factor leading to ablation of plume on afterbody is the flow interference of high speed external flow and high temperature plume. Under certain flying Mach number， the ablation of plume on afterbody will become more serious with the raise of flying altitude. Under certain flying altitude， the ablation of plume on afterbody will become weakened with the increasing of flying Mach number. The simulation results is consistent with the ablation morphology of missile wreckage which validates the correctness of computational method.

Key words： airtoair missile； afterbody； exhaust plume； ablation； numerical simulation

推荐访问： 机尾 空空导弹 数值 发动 分析

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