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| 1 | Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics显示文摘Hypersonic air-breathing propulsion is one of the key techniques for future aviation and the ground aerodynamic testing for full scale test models with sufficient test time at flight conditions is of fundamental importance for verifying hypersonic air-breathing engines.Based on the backward detonation-driven concept,the hypersonic flight-duplicated shock tunnel(or JF-12 shock tunnel)has been successfully constructed and calibrated.This facility is capable of reproducing airflow for Mach numbers ranging from 5 to 9 at an altitude of 25-50 km,with a test duration of more than 100 ms.To quantify the performance of the shock tunnel,experiments were conducted to investigate the aerodynamic characteristics of the test flows and the effects of several critical techniques that play important roles in the operation of the shock tunnel.The stagnation pressure was constant within士5%and the average stagnation pressure varied by less than 0.048%/ms.The variation of the stagnation pressure in repeated experiments is less than 2.0%,indicating the good repeatability of the wind tunnel.The non-uniformity of the Mach number in the core flow field at the nozzle exit was within士2.5%.Additional,a uniform flow field is established upstream of the nozzle exit.The axial gradients of the flow field are small since the Mach number varies less than 1.7%/m.Findings regarding the ignition technology,diaphragm ruptures,detonation driver capacity,incident shock-wave decay,and tunnel operation mode are also presented.The findings of this study are not only helpful for operating the shock tunnel,but can also assist the future development of hypersonic wind tunnels. | C K.Yuan Z.L.Jiang | 2021 | Acta Mechanica Sinica2021，37，3： | 4 |
| 2 | 高超声速高焓条件下的内嵌式温敏漆测量方法显示文摘热流密度点测量结果并不能完全反映详细的热流分布特征,尤其是针对热流梯度较大、热流分布复杂的区域,需要热流密度场测量技术以获取全场精细的热流分布特征.应用温敏漆测量热流密度场的方法得到了广泛应用,但实验条件来流总温较低,与真实飞行环境存在明显差异,真实飞行条件下的辐射效应严重限制了温敏漆技术的应用.针对高超声速高焓条件下缺乏热流密度场测量方法的难题,提出了内嵌式温敏漆测量方法,基本思想是利用温敏漆测量内壁面温度的变化历程结合热传导反问题的求解确定热流密度.本文详细介绍了内嵌式温敏漆测量方法的测量原理、测量系统构成、数据处理方法、设计原则及该测量方法的优势.针对高超声速风洞实验中常见的阶跃、线性和局部突变等热流密度分布进行了数值验证,验证了内嵌式温敏漆测量方法的可行性,并分析了风洞实验温度测量精度及噪声对测量结果的影响.内嵌式温敏漆测量方法可用于测量高超声速真实飞行环境下细致的气动热特征,扩展了温敏漆测量方法的应用范围,解决了高超声速高焓条件下缺乏热流密度场测量方法的难题. | 苑朝凯 姜宗林 | 2022 | 力学学报2022，54，1： | 3 |
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