高超声速圆锥边界层转捩气动热高效预测技术
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南京航空航天大学

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V211.79

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江苏省杰出青年基金(BK20230030)


Efficient prediction method for aerodynamic heating in hypersonic cone boundary-layer transition
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    摘要:

    为了实现不同自由来流下壁面转捩热流场的高效预测,基于变分自编码器架构建立了生成式转捩热流预测模型。选取不同自由来流条件下的圆锥模型作为研究对象,采用数值模拟方法构建转捩热流数据集。搭建变分自编码器模型,在转捩热流数据集上进行了训练和验证,结果分析表明变分自编码器模型能够有效提取热流场隐变量,并精准重构了背风面流向涡转捩的热流场结构。搭建全连接神经网络模型,构建了自由来流与热流场隐变量的非线性映射关系。串联全连接神经网络模型和变分自编码器模型解码器部分,构建高超声速圆锥转捩热流预测模型,预测结果表明,该模型能够有效学习复杂转捩机制作用下的热流分布特征,对不同自由来流下的热流预测精度较高,误差不高于0.024。

    Abstract:

    To enable efficient prediction of transitional heat flux fields under diverse freestream conditions a generative prediction framework based on variational autoencoder architecture was developed. The hypersonic cone configuration was selected as the research object, with Computational Fluid Dynamics simulations being employed to generate the dataset encompassing multiple freestream parameters. The variational autoencoder architecture was systematically trained and validated, demonstrating its capability to extract low-dimensional latent space representations of complex heat flux fields. Particularly, the model was shown to achieve high-fidelity reconstruction of streamwise vortex induced thermal patterns within the leeward-side transition region. A multilayer perceptron was subsequently implemented to establish the nonlinear mapping between freestream parameters and the latent space representations. The integrated prediction model was formed through cascading the multilayer perceptron module with the variational autoencoder decoder. Results demonstrate the prediction accuracy of the heat flux under different free stream is quite perfect, prediction errors not exceeding 0.024 in normalized mean squared error across all test cases, while successfully capturing heat flux distribution features under complex transition mechanisms.

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  • 收稿日期:2025-01-08
  • 最后修改日期:2025-05-06
  • 录用日期:2025-05-07
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