Cold flow research in scramjet combustor

The scramjet combustor cold flow was researched in Northwestern Polytechnical University direct-connected resistance heated facility.The cold flow experimental was performed,for the designed supersonic combustor model with different isolator length,different combustor inflow and different exit back pressure.The combustor inlet Ma=2.0,inflow m=0.73～1.0 kg/s,total pressure pt≈(7～8)×10⁵ Pa,total temperature T_t=300 K.The cold flow field of the supersonic combustor is also simulated with computational fluid dynamics(CFD) software and is analyzed and compared with experimental results.The experimental and computational results show: The length/height ratio of isolator increases,the capacity of resist back pressure for the scramjet combustor increases.The exit pressure distortion of combustor has greater effect on the internal flow field of combustor.The comparison of computational results and experimental results also verify the applicability of numerical simulation method.