In this study,the flow field structure inside a scramjet combustor is numerically simulated using the flamelet/progress variable model.Slope injection is considered,with fuel mixing enhanced by means of a streamwise v...In this study,the flow field structure inside a scramjet combustor is numerically simulated using the flamelet/progress variable model.Slope injection is considered,with fuel mixing enhanced by means of a streamwise vortex.The flow field structure and combustion characteristics are analyzed under different conditions.Attention is also paid to the identification of the mechanisms that keep combustion stable and support enhanced mixing.The overall performances of the combustion chamber are discussed.展开更多
The scope,physical concept,and mathematical model for describing how the rarefaction of the air affects on hypersonic flows have been discussed.A new method,namely the data improved Naive-Stroke(DiNS)model,was propose...The scope,physical concept,and mathematical model for describing how the rarefaction of the air affects on hypersonic flows have been discussed.A new method,namely the data improved Naive-Stroke(DiNS)model,was proposed for the computation of hypersonic shear flows around vehicles flying at altitude of 30-100 km.Validation of the new continuum method has also been done.展开更多
基金This work was supported by the National Natural Science Foundation of China(No.12002193)the Shandong Provincial Natural Science Foundation,China(No.ZR2019QA018).
文摘In this study,the flow field structure inside a scramjet combustor is numerically simulated using the flamelet/progress variable model.Slope injection is considered,with fuel mixing enhanced by means of a streamwise vortex.The flow field structure and combustion characteristics are analyzed under different conditions.Attention is also paid to the identification of the mechanisms that keep combustion stable and support enhanced mixing.The overall performances of the combustion chamber are discussed.
文摘The scope,physical concept,and mathematical model for describing how the rarefaction of the air affects on hypersonic flows have been discussed.A new method,namely the data improved Naive-Stroke(DiNS)model,was proposed for the computation of hypersonic shear flows around vehicles flying at altitude of 30-100 km.Validation of the new continuum method has also been done.
