后掠机翼人工转捩最佳粗糙带高度数值预测

doi:10.7527/S1000-6893.2015.0129

Abstract

Abstract:

A brief introduction to γ-Re_θ transition model based on local variables is presented. The model is applied in predicting the transition on swept wings and in determining the optimal height of the roughness strip in artificial transition and the atmospheric flight Reynolds number which can be simulated by the optimal roughness height. In order to validate the ability of γ-Re_θ model in predicting transition on sweep wings, boundary layer transition on ONERA M6 wing and DLR-F4 standard model wing are predicted, Reynolds-averaged Navier-Stokes(RANS) equations are solved via structured mesh and finite volume method and skin friction coefficient distributions are acquired, thus the transition locations are acquired, which coincide well with the experimental results, conclusions can be made that the predicting results by this model are reliable. Then roughness trips are fixed on DLR-F4 standard model wing surface and transition locations are acquired via the same method, the results reveal that at Mach number of 0.785 and Reynolds number of 3×10⁶, the optimal height of the roughness strip for artificial transition on DLR-F4 standard model wing is 0.11 mm. The simulating ability of artificial transition to atmospheric flight transition is validated by moving the transition location upward via increasing the Reynolds number, results of which indicate that models with the optimal roughness strip height can simulate atmospheric flight free transition at high Reynolds number.

Key words: artificial transition, roughness strip height, transition model, swept wings, Reynolds number, boundary layer

CLC Number:

V211.3

TIAN Yongqiang, ZHANG Zhengke, QU Ke, ZHAI Qi. Numerical prediction of optimal height of roughness strip for artificial transition on swept wings[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 461-474.

References

[1] 范洁川. 风洞试验手册[M]. 北京:航空工业出版社, 2002:313-314. FAN J C. Wind tunnel experiment handbook[M]. Beijing:Aviation Industry Press, 2002:313-314(in Chinese).
[2] 恽起麟. 实验空气动力学[M]. 北京:国防工业出版社, 1991:13-15. YUN Q L. Experimental aerodynamics[M]. Beijing:National Defense Industrial Press, 1991:13-15(in Chinese).
[3] 恽起麟. 风洞实验数据的误差与修正[M]. 北京:国防工业出版社, 1996:276-277. YUN Q L. Wind tunnel experiment data errors and correction[M]. Beijing:National Defense Industrial Press, 1996:276-277(in Chinese).
[4] 程厚梅. 风洞实验干扰与修正[M]. 北京:国防工业出版社, 2003:292-299. CHENG H M. Wind tunnel experiment interference and correction[M]. Beijing:National Defense Industrial Press, 2003:292-299(in Chinese).
[5] LANGTRY R B. A correlation-based transition model using local variables for unstructured parallelized CFD codes[D]. Stuttgart:Stuttgart University, 2006.
[6] MAYLE R E. The role of laminar-turbulent transition in gas turbine engines[J]. ASME Journal of Turbomachinery, 1991, 113(4):509-537.
[7] KLEBANOFF P S, TIDSTROM K D, SARGENT L M. The three-dimensional nature of boundary layer instability[J]. Journal of Fluid Mechanics, 1962, 12(1):1-24.
[8] LEE C B, WU J C. Transition in wall-bonded flows[J]. Applied Mechanics Reviews, 2008, 61(030802):1-21.
[9] LANGTRY R B, MENTER F R. Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes[J]. AIAA Journal, 2009, 47(12):2894-2906.
[10] MALKIEL E, MAYLE R E. Transition in a separation bubble[J]. Journal of Turbomachinery, 1996, 118(4):752-759.
[11] 杨永, 左岁寒, 李喜乐, 等. 基于升华法实验研究后掠翼三维边界层的转捩[J]. 实验流体力学, 2009, 23(3):40-43. YANG Y, ZUO S H, LI X L, et al. Transition studies for the boundary layer on a swept wing based on sublimation technique[J]. Journal of Experiments in Fluid Mechanics, 2009, 23(3):40-43(in Chinese).
[12] 黄勇, 钱丰学, 于昆龙, 等. 基于柱状粗糙元的边界层人工转捩试验研究[J]. 实验流体力学, 2006, 20(3):59-62. HUANG Y, QIAN F X, YU K L, et al. Experimental investigation on boundary layer artificial transition based on transition trip disk[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(3):59-62(in Chinese).
[13] 任旭东, 赵子杰, 高超, 等. 一种新型转捩技术在跨音速风洞中的应用[J]. 实验力学, 2013, 28(3):314-319. REN X D, ZHAO Z J, GAO C, et al. Application of a new transition technology in transition wind tunnel[J]. Journal of Experimental Mechanics, 2013, 28(3):314-319(in Chinese).
[14] 赵子杰, 高超, 张正科. 新型人工转捩技术研究及试验验证[J]. 航空学报, 2015, 36(6):1830-1838. ZHAO Z J, GAO C, ZHANG Z K. Study of an innovative transition technique and its validation through wind tunnel experiments[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(6):1830-1838(in Chinese).
[15] FEY U, EGAMI Y, ENGLER R H. High Reynolds number transition detection by means of temperature sensitive paint:AIAA-2006-0514[R]. Reston:AIAA, 2006.
[16] YORITA D, ASAI K, KLEIN C, et al. Transition detection on rotating propeller blades by means of temperature-sensitive paint:AIAA-2012-1187[R]. Reston:AIAA, 2012.
[17] CHENG T T, ZHANG Z K, QU K, et al. Numerical study of fixed artificial transition and the minimum height of roughness strip for it:AIAA-2013-3093[R]. Reston:AIAA, 2013.
[18] 成婷婷, 张正科, 屈科. 用转捩模型预测转捩及确定最佳粗糙带高度[J]. 航空计算技术, 2012, 42(5):75-79. CHENG T T, ZHANG Z K, QU K. Prediction of transition and optimal roughness height based on transition model[J]. Aeronautical Computing Technique, 2012, 42(5):75-79(in Chinese).
[19] 张玉伦, 王光学, 孟德虹, 等. γ-Re_θ转捩模型的标定研究[J]. 空气动力学学报, 2011, 29(3):295-301. ZHANG Y L, WANG G X, MENG D H, et al. Calibration of γ-Re_θ transition model[J]. Acta Aerodynamica Sinica, 2011, 29(3):295-301(in Chinese).
[20] STOCK H W, HAASE W. Navier-Stokes airfoil computation with e^N transition prediction including transitional flow regions[J]. AIAA Journal, 2000, 38(11):2059-2066.
[21] ZHOU H, ZHAO G F. Flow stability[M]. Beijing:National Defense Industrial Press, 2004:65-67(in Chinese). 周恒, 赵耕夫. 流动稳定性[M]. 北京:国防工业出版社, 2004:65-67.
[22] HERBERT T. Parabolized stability equations[J]. Annual Review of Fluid Mechanics, 1997, 29(1):245-283.
[23] MALIK M R, LI F. Transition studies for swept wing using PSE:AIAA-1993-0077[R]. Reston:AIAA, 1993.
[24] HAYNES T S, READ H L, SARIC W S. CFD validation issues in transition modeling:AIAA-1996-2051[R]. Reston:AIAA, 1996.
[25] LIU Z, ZHAO W, LIU C, et al. Direct numerical simulation of flow transition in high-speed boundary layers around airfoils:AIAA-1997-0753[R]. Reston:AIAA, 1997.
[26] FASEL H F, MEITZ H L, BACHMAN C R. DNS and LES for investigating transition and transtion control:AIAA-1997-1820[R]. Reston:AIAA, 1997.
[27] ANDREAS K. Automatic transition prediction and application to 3D wing configurations:AIAA-2006-0914[R]. Reston:AIAA, 2006.
[28] CORNELIA G, ANDREAS K. Correlation-based transition transport modeling for three-dimensitional aerodynamic configurations[J]. Journal of Aircraft, 2013, 50(5):1533-1539.
[29] NASA. NPARC alliance validation archive[EB/OL].[2014-12-17]. http://www.grc.nasa.gov/WWW/wind/valid/m6wing/m6wing.html.
[30] VASSBERG J C, BUNING P G, RUMSEY C L. Drag prediction for DLR-F4 wing/body using OVERFLOW and CFL3D on overset mesh:AIAA-2002-0840[R]. Reston:AIAA, 2002.
[31] FEY U, EGAMI Y, JANSEN U, et al. Transition detection by temperature sensitive paint at cryogenic temperatures in the European transonic wind tunnel(ETW)[C]//20th International Congress on Instrumentation in Aerospace Simulation Facilities, ICIASF 2003. 2003:77-88.

Numerical prediction of optimal height of roughness strip for artificial transition on swept wings

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Di WANG, Yan LENG, Long YANG, Zhonghua HAN, Zhansen QIAN. Atmospheric turbulence effects on sonic boom propagation based on augmented Burgers equation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626318-626318.
[2]	CHENG Jianrui, SHI Chongguang, QU Lixia, XU Yue, YOU Yancheng, ZHU Chengxiang. Theoretical model of 2D curved shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 125993-125993.
[3]	ZHANG Xingyu, GAO Zhenghong, LEI Tao, MIN Zhihao, LI Weiling, ZHANG Xiaobin. Ground test on aerodynamic-propulsion coupling characteristics of distributed electric propulsion aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125389-125389.
[4]	LIU Qingyang, LEI Juanmian, LIU Zhou, SHI Lei, ZHOU Weijiang. γ-Re_θt-f_Re transition model for compressible flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125794-125794.
[5]	LUO Jiaqi, FU Wenhao, ZENG Xian, XIA Zhiheng. Uncertainty impact of Reynolds number on flow losses of high-lift low-pressure turbine cascade [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125427-125427.
[6]	LIU Qiang, TU Guohua, LUO Zhenbing, CHEN Jianqiang, ZHAO Rui, YUAN Xianxu. Progress in hypersonic boundary layer transition delay control [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 25357-025357.
[7]	TONG Fulin, DONG Siwei, DUAN Junyi, LI Xinliang. Direct numerical simulation of separation bubble in shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125437-125437.
[8]	LIU Jun, LUO Xinfu, WANG Xiansheng. Experiment on influence of leading-edge shape on aerodynamic characteristics of cavity model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125235-125235.
[9]	ZHANG Haoyuan, SUN Dong, QIU Bo, ZHU Yandan, WANG Anling. Influence of turbulent kinetic energy on shock wave/boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125504-125504.
[10]	ZHU Zhibin, SHANG Qing, SHEN Qing. Crossflow modification of transition model for hypersonic boundary layer and its application [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125685-125685.
[11]	LI Qiang, WAN Bingbing, YANG Kai, ZHU Tao. Experimental research on characteristics of pressure and heat flux fluctuation in hypersonic cone boundary layer [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 124956-124956.
[12]	NIU Xiaotian, LI Jie, ZHOU Zhipeng, YANG Zhao, CHANG Mochen. Sensitivity analysis of transonic laminar flow characteristics of an aircraft with laminar wing section [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526771-526771.
[13]	TANG Songxiang, LI Jie, ZHANG Heng, NIU Xiaotian. Aerodynamic performance optimization design of middle wing section of a special laminar unmanned flight in high-speed cruise [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526766-526766.
[14]	YANG Zhao, LI Jie, NIU Xiaotian. Analysis and correction of Reynolds number effect of a flight verification platform with laminar wing section [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 527287-527287.
[15]	GUO Qiuting, SUN Yan, GUO Zheng, LIU Guangyuan. Separation method for Reynolds number/static aeroelastic coupling effect in wind tunnel test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526312-526312.