摘要
为验证从超音速混合层中发展而来的修正可压缩性(包括膨胀可压缩性和结构可压缩性两部分)的k-ε湍流模型对复杂超音速流场的预测能力,对复杂的超音速燃烧冲压发动机(Scramjet)燃烧室冷态流场进行数值模拟.将修正k-ε模型、标准k-ε模型以及标准k-ωSST模型的计算结果与实验结果进行了对比.结果表明,修正k-ε模型能够较好地预测该复杂流场,对湍流动能的预测改进较大,优于k-ωSST的结果,与实验吻合得较好;壁面压力分布以及速度分布在激波附近修正明显,与实验结果更加吻合.
Numerical simulations were preformed in a complex supersonic combustion ramjet （Scramjet） combustor cold field to evaluate the performance of the modified k-ε turbulence model originally developed from the compressible mixing layers. Predicted results with the modified /k-ε model, standard /k-ε model and standard k-ω SST model were compared with experimental data respectively. The modified model gives quite reasonable resolution of the complex supersonic flow structures and significantly improves the result of turbulent kinetic energy, better than by the k-ω SST model and matching the experiment well. Predictions of wall pressure and velocity are improved in the region near the shock waves, and have better agreement with experimental data.
基金
国家自然科学基金(50776085)
中国空气动力研究与发展中心资助
