转捩模式与试验在高超声速边界层转捩中的应用研究

Application of Transition Mode and Experiment on Hypersonic Boundary Layer Transition

高超声速飞行器前体下表面及压缩面组合外形的转捩预测问题是飞行器气动和结构设计中的重要问题。本文改进了k-ω-γ转捩模式,采用数值模拟方法预测转捩发生位置,并采用基于纳米示踪的平面激光散射(NPLS)技术和温敏漆(TSP)技术对转捩开展试验。模拟得到的转捩位置与试验得到的转捩位置一致,验证了本文发展的转捩预测方法的准确性与可靠性。转捩发生在模型的前体下表面,转捩位置在展向的分布是不均匀的,并呈现出对称形式。本文介绍的两种预测方案为工程转捩预测提供了可行的解决方案。

In the aerodynamic and structural design of aircraft,the hypersonic transition's prediction on the lower surface of the forebody and the compression is a significant problem.This paper improves the transition mode and uses the improved k-ω-γmodel to predict in predicting the transition location.Also,the transition process is studied via nanotracer planar laser scattering(NPLS)technique and temperature sensitive paint(TSP)technique.The transition location predicted by both simulation and experiment is consistent,which verifies the accuracy and the reliability of the current methods.The transition is located on the lower surface of the forebody.The distribution of transition positions in the spanwise direction is not uniform and is symmetrical.The method studied in this paper provides a practical solution for the engineering transition prediction.