Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime

Liu Zhiyong; Li Jianqiang; Gao Rongzhao; Tao Yang; Liang Jinmin; Zhang Changfeng

doi:10.11729/syltlx20180032

Volume 32 Issue 5

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2018 > 32(5): 76-81

Liu Zhiyong, Li Jianqiang, Gao Rongzhao, et al. Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 76-81. doi: 10.11729/syltlx20180032

Citation:

PDF( 5376 KB)

Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime

doi: 10.11729/syltlx20180032

High Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2018-03-09
Rev Recd Date: 2018-06-27
Publish Date: 2018-10-25

Abstract

Abstract

Measurements of skin friction on a flat plate model were conducted in the 0.6m×0.6m subsonic/transonic/supersonic wind tunnel. Oil film interferometry (OFI) and Preston tube technique were applied to obtain the skin friction data at Ma=0.4~0.8. In order to avoid flow separation, an elliptical leading edge was employed. Results indicate that the agreement between OFI and Preston tube is very well. Viscosity of oil film has little influence on the skin friction measurement. When the stream's Mach number or the total pressure changes, the skin friction coefficient decreases along with the increase of the dynamic pressure or the product of Mach number and Reynolds number (Ma·Re). A freckle-like interference pattern was observed at Ma=0.4 and 0.6, and an assumption based on the new pattern was proposed to determine the transition location. According to the oil motion and CFD results, a separation bubble rather than the new pattern appears at Ma=0.8, and it is responsible for the transition of boundary layer.
- OFI,
- Preston tube,
- skin friction,
- transition,
- separation

FullText(HTML)

References(19)

References

[1]	Schrauf G. Status and perspectives of laminar flow[J]. The Aeronautical Journal, 2005, 109(1102):639-644. doi: 10.1017/S000192400000097X
[2]	Patel V C. Calibration of the Preston tube and limitations on its use in pressure gradients[J]. Journal of Fluid Mechanics, 1965, 23(1):185-208. doi: 10.1017/S0022112065001301
[3]	Jerry M Allen. Evaluation of Preston tube calibration equations in supersonic flow[J]. AIAA Journal, 1973, 11(11):1461-1462. doi: 10.2514/3.50610
[4]	Bechert D W. Calibration of Preston tubes[J]. AIAA Journal, 1996, 34(1):205-206. doi: 10.2514/3.13048
[5]	KimK S, Lee Y, Settles G S. Laser interferometer/Preston tube skin-friction comparison in shock/boundary-layer interaction[J]. AIAA Journal, 1991, 29(6):1007-1009. doi: 10.2514/3.10695
[6]	Kwak D Y, Yoshida K, Noguchi M, et al. Boundary layer transition measurement using Preston tube on NEXST-1 flight test[C]//Proc of 25th AIAA Applied Aerodynamics Conference. 2007.
[7]	DriverD M, Drake A. Skin friction measurements using oil film interferometry in the 11' transonic wind tunnel at NASA Ames[C]//Proc of 42nd AIAA Aerospace Sciences Meeting and Exhibit. 2004.
[8]	Ehrmann R S, Lichtwardt J A, Paciano E N, et al. Global skin friction measurements on a circulation control airliner in the NFAC[C]//Proc of 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2013.
[9]	Schülein E. Optical skin friction measurements in short-duration facilities[C]//Proc of 24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, Portland. 2004.
[10]	Garrison T J, Ackman M. Development of a global interferometer skin-friction meter[J]. AIAA Journal, 1998, 36(1):62-68. doi: 10.2514/2.352
[11]	代成果, 张长丰, 黄飓, 等.高超声速表面摩擦应力油膜干涉测量技术研究[J].实验流体力学, 2012, 26(2):68-71, 85. http://www.syltlx.com/CN/abstract/abstract10563.shtml Dai C G, Zhang C F, Huang J. et al. Hypersonic skin friction stress measurements using oil film interferometry technique[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(2):68-71, 85. http://www.syltlx.com/CN/abstract/abstract10563.shtml
[12]	刘志勇, 张长丰, 代成果.表面摩擦应力油膜干涉测量技术在Ma=8的应用[J].实验流体力学, 2015, 29(6):74-78. http://www.syltlx.com/CN/abstract/abstract10893.shtml Liu Z Y, Zhang C F, Dai C G. Application of oil film interfero-metry technique at Ma=8[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(6):74-78. http://www.syltlx.com/CN/abstract/abstract10893.shtml
[13]	丁超, 史志伟, 玉曜瑜.基于油膜干涉法的表面摩擦应力测量技术研究[J].实验力学, 2011, 26(6):707-714. http://d.old.wanfangdata.com.cn/Periodical/sylx201106011 Ding C, Shi Z W, Yu Y Y. Study of skin friction stress mea-surement technique based on oil film interferometry[J]. Journal of Experimental in Fluid Mechanics, 2011, 26(6):707-714. http://d.old.wanfangdata.com.cn/Periodical/sylx201106011
[14]	耿子海, 史志伟, 金启刚.油膜干涉测量翼型壁面摩阻低速风洞试验技术[J].空气动力学学报, 2016, 34(1):80-85. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601014 Geng Z H, Shi Z W, Jin Q G. Invetigation of skin-friction measurements using oil-film interferometry on airfoil wall in low speed wind tunnel[J]. Acta Aerodynamica Sinica, 2016, 34(1):80-85. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601014
[15]	Bhatia D, Yang G J, Sun J, et al. Effects of different geometries on boundary layer transition[C]//Proc of 54th AIAA Aerospace Sciences Meeting. 2016.
[16]	Squire L C. The motion of a thin oil sheet under the steady boundary layer on a body[J]. Journal of Fluid Mechanics, 1961, 11:161-179. doi: 10.1017/S0022112061000445
[17]	Fenter F W, Stalmach C J Jr. The measurement of local turbulent skin friction at supersonic speeds by means of surface impact pressure probes[R]. Defense Research Laboratory Report, No. 392, CM-878, 1957.
[18]	Naughton J W. Multiple-image oil film interferometry[C]//Proc of 46th AIAA Aerospace Sciences Meeting and Exhibit. 2008.
[19]	Naughton J W, Liu T. Photogrammetry in oil-film interferometry[J]. AIAA Journal, 2007, 45(7):1620-1629. doi: 10.2514/1.24634