航空学报 > 2015, Vol. 36 Issue (1): 325-345   doi: 10.7527/S1000-6893.2014.0242

高超声速气动热预测技术及发展趋势

彭治雨, 石义雷, 龚红明, 李中华, 罗义成   

  1. 中国空气动力研究与发展中心, 绵阳 621000
  • 收稿日期:2014-07-23 修回日期:2014-10-08 出版日期:2015-01-15 发布日期:2014-10-09
  • 通讯作者: 彭治雨,Tel.: 0816-2465017 E-mail: pengzhiyu65536@163.com E-mail:pengzhiyu65536@163.com
  • 作者简介:彭治雨 男,硕士,研究员。主要研究方向:高超声速气动热研究。 Tel: 0816-2465017 E-mail: pengzhiyu65536@163.com

Hypersonic aeroheating prediction technique and its trend of development

PENG Zhiyu, SHI Yilei, GONG Hongming, LI Zhonghua, LUO Yicheng   

  1. China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2014-07-23 Revised:2014-10-08 Online:2015-01-15 Published:2014-10-09

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。

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

Abstract:

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.

Key words: hypersonic, vehicle, aeroheating, engineering computation method, numerical simulation, experiment technique

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