The numerical simulation and test verification of the inlet total pressure distortion of a core aero-engine
The inlet total pressure distortion test was carried out on a core aero-engine for the first time.Before the formal test,the total pressure distribution of the aerodynamic interface under different inlet states and positions was simulated by commercial software and the results were compared with the experiment.The results show that the distribution of the circular total pressure distortion measured by the 8 probes of the aerodynamic interface is consistent with the simulation results,with a maximum error of 2.1%,which occurs at the 4th probe in the calculated states 95%,plate position 24%.The correctness of numerical calculation method was verified,which provided reference for the design and verification of inlet total pressure distortion tests of models,as well as support for the following inlet total pressure distortion test of other models.
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