高马赫数飞行器研究对宽速域转捩实验提出了迫切需求，转捩实验要求风洞能复现飞行环境。近年来国内外针对高马赫数低扰动风洞开展了较为深入的研究，但仍不能达到宽速域转捩实验要求，特别是对温度模拟不足。然而近期研究表明，温度效应对转捩影响不容忽视，而现有设备均不能兼顾低扰动（考虑“涡波”、“声波”及“熵波”）和宽马赫数运行要求。本项目基于管风洞原理，探索一种综合运用电阻预加热与慢活塞绝热压缩叠加驱动的新型宽马赫数风洞设计技术，以期复现M2~6飞行环境。重点研究三方面内容：开展新型宽马赫数低扰动复现风洞设计理论研究，建立活塞轨迹及性能预测方法；发展不确定量化分析方法，建立不确定因素与扰动特性量化关系；基于层流双喷管结构，针对主要扰动源，开展抑制技术研究和效果分析。将采用理论分析、先进数值方法相结合的手段，完善宽马赫数设备设计理论，可为高马赫数飞行器研制提供设备技术支撑、为气动试验数据分析应用提供依据。

The temperature effect on the transition can not be ignored with the development of high Mach number aircrafts. The wind tunnel should reproduce the wide speed range flight environment for transition experiments, while the existing ground facilities can not take into account the low disturbance (considering "vortex wave", "sound" and "entropy wave") and wide-range Mach numbers operation. A novel facility is proposed in this project based on the Ludwieg tube with resistance preheating and slow-piston adiabatic compression. This program devotes to: develop a computationally efficient method to predict the piston trajectory and characterize the facility operation condition; develop a non-embedded uncertainty quantification analysis method and establish quantitative relationship between uncertain factors and disturbance characteristics; carry out the main disturbance source and identify possible mitigation techniques based on the structure of laminar-double nozzles. The design theory of wide-range Mach number facilities will be improved by numerical simulation and theoretical analysis. This program can provide technical support for the development of high Mach number aircrafts and provide the basis for the analysis and application of experimental data.