高超声速气动热预测技术及发展趋势  

Hypersonic aeroheating prediction technique and its trend of development

作　　者：彭治雨[1] 石义雷[1] 龚红明[1] 李中华[1] 罗义成[1] 

机构地区：[1]中国空气动力研究与发展中心,绵阳621000

出　　处：《航空学报》2015年第1期325-345,共21页Acta Aeronautica et Astronautica Sinica

摘　　要：高超声速气动热预测技术是高超声速飞行器发展的关键技术之一。对高超声速气动热预测技术的发展情况进行了分析探讨。首先,简要回顾了国内外高超声速气动热理论预测及地面实验技术的发展历程;在此基础上,结合典型外形的计算与风洞试验结果的比较,重点介绍分析了气动热工程计算方法、数值模拟方法、气动热风洞试验设备的模拟能力及目前实验测试技术的研究水平;最后,对气动热预测技术的发展趋势进行了讨论,提出了气动热预测技术应研究解决的问题。The hypersonic aeroheating prediction is a key technique for hypersonic vehicle. Development of hypersonic aeroheating prediction technique is analyzed and discussed. Firstly, a brief development history of hypersonic aeroheating prediction technique and experiment technology is reviewed. Based on that, according to the comparison with the calculation and wind tunnel experiment results for typical configuration, the aeroheating engineering computation calculation method and numerical simulation prediction technique are introduced with emphasis; meanwhile the performance of ground experiment equipment and the status quo of measurement technique are also generalized. Finally, the development trend of hypersonic aeroheating prediction technique is discussed; and the issue need to be studied and solved on aeroheating prediction technique are also raised.

关 键 词：高超声速 飞行器 气动热 工程计算方法 数值模拟 实验技术 

分 类 号：V434.11[航空宇航科学与技术—航空宇航推进理论与工程]