气动热环境下喷管射流流场模拟

Nozzle Jet Flow Field Simulation of Aerodynamic Heating Environment

采用Witoszynski、Foelsch法及边界层修正量等因素对(4～6)马赫喷管型线进行设计,将所设计喷管射流及实验区流场环境进行模拟;通过改变喷管实验区入出口压力比,探讨最佳稳定流场时所对应的入出口压力比。为明确风洞实验中构件附近流场的准确分布,在实验区放置球锥模型,对比分析所设计喷管射流场及远场边界条件下的流场品质,探究实验区壁面及喷管模型对稳定气流的影响大小。同时,分析球锥构件半锥角的改变对喷管实验区射流的影响。研究结果表明:所设计喷管及实验区的流场都能保证高马赫、高品质稳定气流,验证了喷管型线设计的合理;两种环境下球锥模型附近的速度场、温度场及压力场分布差异明显,实现后续模拟构件在风洞实验的高温应变及模态等特性的结果更精确;喷管实验区流场中不同半锥角的构件温度分布规律结果对飞行器头部热防护的措施可提供理论参考。

Witoszynski、Foelsch boundary correction method and other factors were designed a nozzle type lines of(4~6)Ma,and designed to simulate the jet nozzle flow field and experimental environment;By varying the experimental area into the outlet nozzle pressure ratio to explore the best steady flow field when the corresponding inlet and outlet pressure ratio.In order to clarify the accurate distribution of the flow field near the component in the wind tunnel experiment,the spherical cone model was set up in the experimental area,and the flow field quality of the nozzle jet field and far field boundary condition were compared and analyzed,which were to explore and experiment area nozzle wall model steady airflow effect size.Meanwhile,by varying the half cone angle of the ball member to analyze the experimental area of the nozzle flow field effect size.The results show that the designed nozzle and the experimental flow field can guarantee the stability of high Mach,high quality air,to verify the design of reasonable nozzle contour line;Ball cone model under two kinds of environment near the velocity field,temperature field and stress field distribution differences,achieve the subsequent simulation component in wind tunnel experiment of high temperature strain and modal characteristics of the result more accurate;Nozzle flow field in the different experimental spot half taper Angle of component temperature distribution results on the aircraft head thermal protection measures can provide theoretical reference.