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LI Chengrui, JIANG Zhongzheng, WU Changju, et al. Hypersonic modification and verification of Langtry-Menter transition model[J]. Journal of Aerospace Power, 2024, 39(X):20220970 doi: 10.13224/j.cnki.jasp.20220970
Citation: LI Chengrui, JIANG Zhongzheng, WU Changju, et al. Hypersonic modification and verification of Langtry-Menter transition model[J]. Journal of Aerospace Power, 2024, 39(X):20220970 doi: 10.13224/j.cnki.jasp.20220970

Hypersonic modification and verification of Langtry-Menter transition model

doi: 10.13224/j.cnki.jasp.20220970
  • Received Date: 2022-12-22
    Available Online: 2024-02-29
  • For the prediction of hypersonic boundary layer transition flow, three types of high-speed modified methods were studied based on the traditional Langtry-Menter transition model and SST (shear stress transport) turbulence model. The modification of hypersonic cross-flow criterion, compressibility modification of turbulent kinetic energy pressure dilatation term and modification of pressure gradient coefficient were introduced into the original transition model to expand the simulation capacity of the model in hypersonic flow. The modified transition model was validated by using several typical cases: supersonic plate, hypersonic cone with zero angle of attack, hypersonic cone with small angle of attack and hypersonic HIFIRE-5. The results showed that the predicted transition-start position, transition-end position and transition zone length of the modified model were basically consistent with the experimental results. The calculated results of skin friction and heat flux were basically consistent with the experimental measurement data. The modified transition model performed well in predicting hypersonic transition flow.

     

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