高马赫数层流摩阻数值计算精度

doi:10.7527/S1000-6893.2021.25737

国家数值风洞(NNW)进展及应用专栏

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高马赫数层流摩阻数值计算精度

范月华, 段毅, 周乃桢, 杨攀

中国运载火箭技术研究院空间物理重点实验室, 北京 100076

收稿日期:2021-03-30 修回日期:2021-04-29 发布日期:2021-05-31
通讯作者: 段毅 E-mail:duanyeebj@163.com
基金资助:
国家数值风洞工程

Friction numerical calculation precision in high Mach number laminar flow

FAN Yuehua, DUAN Yee, ZHOU Naizhen, YANG Pan

Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China

Received:2021-03-30 Revised:2021-04-29 Published:2021-05-31
Supported by:
National Numerical Windtunnel Project

摘要/Abstract

摘要： 飞行器在高空高速飞行时黏性效应显著，摩阻预示精度对飞行器的关键气动性能意义重大。目前，摩阻预示主要依赖数值计算，但高马赫数层流摩擦阻力计算与试验测量结果仍存在差距。以具有高速飞行器典型部件特征的球锥、三角翼为对象，结合风洞试验摩阻测量结果，使用国家数值风洞（NNW）数值计算软件和自研CFD程序研究了数值计算中影响摩阻计算精度的格式数值耗散及壁面温度边界条件等重要因素。研究结果表明：数值耗散越小，表面摩阻的计算精度越高；在速度较低的边界层近壁区内关闭熵修正，将有助于提高表面摩阻的预示精度。此外，在高马赫数流动问题的数值模拟中，壁面温度条件对表面摩阻计算同样具有重要影响。最后，基于分析结果和工程需要提出了对高精度摩阻数值预示的研究需求。

关键词: 高马赫数, 层流, 摩阻计算, 数值耗散, 边界条件, NNW-Flowstar

Abstract: The prominent viscous effect of vehicles flying at a high speed and altitude leads to the necessity of precise skin friction prediction for the key aerodynamic performance of the vehicles. However, the skin friction obtained from numerical calculation, currently the main approach to skin friction prediction, has a large gap from that of the tunnel test in the high Mach number laminar flow. The key factors influencing friction numerical prediction precision such as numerical dissipation of the space scheme and wall temperature boundary conditions were studied. With typical characteristics of high speed vehicles, a cone with a sharp nose and a delta wing were investigated considering the tunnel test results in the study. The results showed that less numerical dissipation results in more accurate skin friction calculation, and that closing the entropy fix in regions near the wall in the boundary layer helps to improve the calculation precision of skin friction. Additionally, the wall temperature boundary conditions also have an important effect on the skin friction calculation in the high Mach number flow. Finally, the requirements for high-precision skin friction numerical prediction are proposed based on the analysis results and engineering demands.

Key words: high Mach number, laminar flow, friction calculation, numerical dissipation, boundary conditions, NNW-Flowstar

中图分类号:

V211.3

范月华, 段毅, 周乃桢, 杨攀. 高马赫数层流摩阻数值计算精度[J]. 航空学报, 2021, 42(9): 625737-625737.

FAN Yuehua, DUAN Yee, ZHOU Naizhen, YANG Pan. Friction numerical calculation precision in high Mach number laminar flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(9): 625737-625737.

参考文献

[1] 张益荣, 张毅锋, 解静, 等. 典型高超声速翼身组合体粘性干扰效应模型研究[J]. 空气动力学学报, 2017, 35(2):186-191. ZHANG Y R, ZHANG Y F, XIE J, et al. Study of viscous interaction effect model for typical hypersonic wing-body figuration[J]. Acta Aerodynamica Sinica, 2017, 35(2):186-191(in Chinese).
[2] 史云龙. 高超声速风洞模型表面摩阻测量技术研究[D]. 绵阳:中国空气动力研究与发展中心, 2015:8-10. SHI Y L. The research of model skin friction measurement technology in hypersonic wind tunnel[D].Mianyang:China Aerodynamics Research and Development Center, 2015:8-10(in Chinese).
[3] 马洪强, 高贺, 毕志献. 高超声速飞行器相关的摩擦阻力直接测量技术[J]. 实验流体力学, 2011, 25(4):83-88. MA H Q, GAO H, BI Z X. Direct measurement of skin friction for hypersonic flight vehicle[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(4):83-88(in Chinese).
[4] 吕治国, 李国君, 赵荣娟, 等. 激波风洞高超声速摩阻直接测量技术研究[J]. 实验流体力学, 2013, 27(6):81-85. LV Z G, LI G J, ZHAO R J, et al. Direct measurement of skin friction at hypersonic shock tunnel[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(6):81-85(in Chinese).
[5] BUI T, PIPITONE B, KRAKE K. In-flight capability for evaluating skin-friction gages and other near-wall flow sensors:AIAA-2003-0741[R]. Reston:AIAA, 2003.
[6] 唐志共, 张益荣, 陈坚强, 等. 更准确、更精确、更高效:高超声速流动数值模拟研究进展[J]. 航空学报, 2015, 36(1):120-134. TANG Z G, ZHANG Y R, CHEN J Q, et al. More fidelity, more accurate, more efficient-Progress on numerical simulations for hypersonic flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):120-134(in Chinese).
[7] 周铸, 黄江涛, 黄勇, 等. CFD技术在航空工程领域的应用、挑战与发展[J]. 航空学报, 2017, 38(3):020891. ZHOU Z, HUANG J T, HUANG Y, et al. CFD technology in aeronautic engineering field:Applications, challenges and development[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(3):020891(in Chinese).
[8] 周丹, 禹建军, 阎超. 层流平板摩擦阻力的数值计算[J]. 北京航空航天大学学报, 2007, 33(6):663-667. ZHOU D, YU J J, YAN C. Numerical calculation of laminar flat plate skin friction[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(6):663-667(in Chinese).
[9] 郑世超. 高精度格式在高超声速流动数值模拟中的验证与确认研究[D]. 长沙:国防科学技术大学, 2016:42-49. ZHENG S C. Verification and validation study of high order schemes in numerical simulations of hypersonic flows[D]. Changsha:National University of Defense Technology, 2016:42-49(in Chinese).
[10] 张培红, 张耀冰, 周桂宇, 等. 面向混合网格高精度阻力预测的熵修正方法[J]. 航空学报, 2018, 39(9):122030. ZHANG P H, ZHANG Y B, ZHOU G Y, et al. Entropy correction method for high accuracy drag prediction with mixed grids[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(9):122030(in Chinese).
[11] MERITT R J, SCHETZ J A, MARINEAU E C, et al. Direct measurements of skin friction at AEDC hypervelocity wind tunnel 9:AIAA-2015-1914[R]. Reston:AIAA, 2015.
[12] 陈坚强. 国家数值风洞(NNW)工程关键技术研究进展[J/OL]. 中国科学:技术科学, (2021-04-28)[2021-05-17]. https://kns.cnki.net/kcms/detail/11.5844.TH.20210-428.0914.006.html. CHEN J Q. Advances in the key technologies of Chinese national numericalwindtunnel project[J/OL]. Scientia Sinica Technologica, (2021-04-28)[2021-05-17]. https://kns.cnki.net/kcms/detail/11.5844.TH.20210428.0914.006.html (in Chinese).
[13] TORO E F, SPRUCE M, SPEARES W. Restoration of the contact surface in the HLL-Riemann solver[J]. Shock Waves, 1994, 4(1):25-34.
[14] ROE P L. Approximate Riemann solvers, parameter vectors, and difference schemes[J]. Journal of Computational Physics, 1981, 43(2):357-372.
[15] LIOU M S, STEFFEN C J. A new flux splitting scheme[J]. Journal of Computational Physics, 1993, 107(1):23-39.
[16] LIOU M S. A sequel to AUSM:AUSM+[J]. Journal of Computational Physics, 1996, 129(2):364-382.
[17] VAN LEER B. Flux vector splitting for Euler equations[J]. Lecture Notes in Physics, 1982, 170:507-512.
[18] VAN LEER B. Towards the ultimate conservative difference scheme.V.A second-order sequel toGodunov's method[J]. Journal of Computational Physics, 1979, 32(1):101-136.
[19] 陈坚强, 张益荣, 郭勇颜. 高超声速流动数值模拟方法及应用[M]. 北京:科学出版社, 2019:43-44. CHEN J Q, ZHANG Y R, GUO Y Y. Numerical simulation methods and applications of hypersonic flow[M]. Beijing:Science Press, 2019:43-44(in Chinese).
[20] 阎超. 计算流体力学方法及应用[M]. 北京:北京航空航天大学出版社, 2006:83-84. YAN C.Methods and applications of computational fluid dynamics[M]. Beijing:Beihang University Press, 2006:83-84(in Chinese).
[21] MVLLER B. Simple improvements of an upwind TVD scheme for hypersonic flow[C]//9th Computational Fluid Dynamics Conference. Reston:AIAA, 1989.
[22] YEE H C, KLOPFER G H, MONTAGNÉ J L. High-resolution shock-capturing schemes for inviscid and viscous hypersonic flows[J]. Journal of Computational Physics, 1990, 88(1):31-61.
[23] ANDERSON J D. 高超声速和高温气体动力学[M]. 杨永, 李栋, 译. 北京:航空工业出版社, 2013:235-252. ANDERSON J D.Hypersonic and high-temperature gas dynamics[M]. YANG Y, LI D, translated. Beijing:Aviation Industry Press, 2013:235-252.

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高马赫数层流摩阻数值计算精度

Friction numerical calculation precision in high Mach number laminar flow

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