西北工业大学 航空学院,西安,710072
魏斌斌*(1990-),男,博士,研究方向:实验空气动力学. E-mail:weibinbin123@mail.nwpu.edu.cn
纸质出版:2022
移动端阅览
魏斌斌, 高永卫, 孙博, 等. 翼型边界层脉动压力统计特征分析[J]. 空气动力学学报, 2022, 40(6): 129−137.
WEI Binbin, GAO Yongwei, SUN Bo, et al. Statistical characteristics analysis of fluctuating pressure in airfoil boundary layer[J]. 2022, 40(6): 129-137.
魏斌斌, 高永卫, 孙博, 等. 翼型边界层脉动压力统计特征分析[J]. 空气动力学学报, 2022, 40(6): 129−137. DOI: 10.7638/kqdlxxb-2021.0263
WEI Binbin, GAO Yongwei, SUN Bo, et al. Statistical characteristics analysis of fluctuating pressure in airfoil boundary layer[J]. 2022, 40(6): 129-137. DOI: 10.7638/kqdlxxb-2021.0263.
为了研究物面边界层流态的脉动特征,使用脉动压力方法对翼型边界层进行了自然转捩探测,深入研究了翼型边界层不同流态的脉动压力统计特征,包括均方根值
σ
、偏度
s
、陡度
k
和信息熵
I
,绘制了不同流态的(
s
,
k
)相图。研究表明:层流信息的偏度与Gauss分布的偏度接近,湍流信息的陡度与Gauss分布的陡度接近,而转捩在(
s
,
k
)相图上的分布与Gauss分布相差较大。文章详细推导了
I
与
σ
、
s
、
k
之间的数学关系,建立了
I
与
σ
、
s
、
k
之间的显式表达式,从而将用于转捩判断的一维决策空间扩展为了四维决策空间(
σ
,
s
,
k
,
I
)。研究成果有助于人们深刻理解脉动压力信息熵与一般统计量之间的内在关系,同时对后续的数据分析、分类模型建立以及规则提取等也有一定帮助。
To study the fluctuated characteristics of the boundary layer
the transition on an airfoil was detected using the fluctuating pressure method in this paper
and the statistical characteristics of the fluctuating pressure in different flow states
including the root mean square (RMS) value
σ
skewness
s
kurtosis
k
and information entropy
I
were deeply investigated. The (
s
k
) phase diagrams of different flow states were presented. The results showed that skewness of the laminar state was close to that of G
auss distribution and kurtosis of the turbulent state was close to that of Gauss distribution
while the distribution in the (
s
k
) phase diagram of the transition state was quite different from the Gauss distribution. The mathematical relationship between
I
and
k
σ
s
was deduced in detail and an explicit expression was established
such that the one-dimensional decision space for the transition detection was extended to a four-dimensional decision space (
σ
s
k
I
). This work is useful to deeply understand the internal relationship between the information entropy and the general statistics of fluctuating pressure
and is also of help to subsequent data analysis
classification model establishment and rule extraction.
GAO Y W, ZHU Q L, WANG L. Measurement of unsteady transition on a pitching airfoil using dynamic pressure sensors[J]. Journal of Mechanical Science and Technology, 2016, 30(10): 4571-4578. DOI:10.1007/s12206-016-0928-5
KNAPP C F, ROACHE P J. A combined visual and hot-wire anemometer investigation of boundary-layer transition[J]. AIAA Journal, 1968, 6(1): 29-36. DOI:10.2514/3.4437
LAGRAFF J E. Observations of hypersonic boundary-layer transition using hot wire anemometry[J]. AIAA Journal, 1972, 10(6): 762-769. DOI:10.2514/3.50208
COSTANTINI M, FEY U, HENNE U, et al. Nonadiabatic surface effects on transition measurements using temperature-sensitive paints[J]. AIAA Journal, 2015, 53(5): 1172-1187. DOI:10.2514/1.J053155
FEY U, EGAMI Y, KLEIN C. Temperature-sensitive paint application in cryogenic wind tunnels: transition detection at high Reynolds numbers and influence of the technique on measured aerodynamic coefficients[C]//Proc of the 2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities, Pacific Grove, CA, USA. IEEE, 2007: 1-17. doi: 10.1109/ICIASF.2007.4380904
HODSON H, HOWELL R. Unsteady flow: Its role in the low pressure turbine[C]// 9th International Symposium Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachine. Lyon, France, 2000.
ZHANG X F, MAHALLATI A, SJOLANDER S. Hot-film measurements of boundary layer transition, separartion and reattachment on a low-pressure turbine airfoil at low Reynolds numbers[C]// 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Indianapolis, Indiana. Reston, Virginia: AIAA, 2002 doi: 10.2514/6.2002-3643
BURGMANN S, DANNEMANN J, SCHRÖDER W. Time-resolved and volumetric PIV measurements of a transitional separation bubble on an SD7003 airfoil[J]. Experiments in Fluids, 2008, 44(4): 609-622. DOI:10.1007/s00348-007-0421-0
LEE T, GERONTAKOS P. Investigation of flow over an oscillating airfoil[J]. Journal of Fluid Mechanics, 2004, 512. DOI:10.1017/s0022112004009851
LEE T, BASU S. Measurement of unsteady boundary layer developed on an oscillating airfoil using multiple hot-film sensors[J]. Experiments in Fluids, 1998, 25(2): 108-117. DOI:10.1007/s003480050214
RICHTER K, KOCH S, GARDNER A D, et al. Experimental investigation of unsteady transition on a pitching rotor blade airfoil[J]. Journal of the American Helicopter Society, 2014, 59(1): 1-12. DOI:10.4050/jahs.59.012001
KIM D H, CHANG J W. Reynolds number effects on unsteady boundary layer of an oscillating airfoil[C]// 27th AIAA Applied Aerodynamics Conference, San Antonio, Texas. Reston, Virginia: AIAA, 2009 doi: 10.2514/6.2009-3501
HAGHIRI A A, MANI M, FALLAHPOUR N. Unsteady boundary layer measurement on an oscillating (pitching) supercritical airfoil in compressible flow using multiple hot-film sensors[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2015, 229(10): 1771-1784. DOI:10.1177/0954410014560380
IKAMI T, FUJITA K, NAGAI H, et al. Measurement of boundary layer transition on oscillating airfoil using cntTSP in low-speed wind tunnel[C]// AIAA Scitech 2020 Forum, Orlando, FL. Reston, Virginia: AIAA, 2020 doi: 10.2514/6.2020-0294
HELLER H H. Acoustic technique for detection of flow transition on hypersonic re-entry vehicles[J]. AIAA Journal, 1969, 7(12): 2227-2232. DOI:10.2514/3.5520
LEWIS T L, BANNER R D. Boundary layer transition detection on the x-15 vertical fin using surface-pressure-fluctuation measurements: NASA TM X-2466[R]. 1971.
WEI B B, GAO Y W, WANG L, et al. Analysis of flow transition and separation on oscillating airfoil by pressure signature[J]. Journal of Mechanical Science and Technology, 2019, 33(1): 279-288. DOI:10.1007/s12206-018-1227-0
WEI B B, GAO Y W, LI D, et al. Variable slip window technology in transition detection on pitching airfoil[J]. Chinese Journal of Aeronautics, 2020, 33(4): 1166-1180. DOI:10.1016/j.cja.2019.12.028
WANG M, GAO Y W, ZHU Q L. An investigation on data processing in transition detection using surface pressure fluctuation[J]. Journal of Experimental Mechanics, 2012, 27(6): 764-770. (in Chinese)
GAO Y W, HUANG P, ZHU Q L, et al. Experimental study on pressure fluctuation sensor-based diagnostic for boundary layer transition with long-fine tubing system[J]. Journal of Experiments in Fluid Mechanics, 2014, 28(6): 98-103. (in Chinese)
WANG K L, FENG G W, ZHOU M D. A preliminary study on a new technique to determine klebannoff transition[J]. Acta Aeronautica et Astronautica Sinica, 1987, 8(3): 184-188. (in Chinese)
ZHENG G F. Effect of the turbulence on boundary layer transition measurement[J]. Acta Aeronautica et Astronautica Sinica, 1992, 13(2): 53-56. (in Chinese)
STOCK H W, HAASE W. Feasibility study of e exp N transition prediction in Navier-Stokes methods for airfoils[J]. AIAA Journal, 1999, 37: 1187-1196. DOI:10.2514/3.14308
KOTSONIS M, VAN INGEN J. A two-parameter method for eN transition prediction[C]// 6th AIAA Theoretical Fluid Mechanics Conference, Honolulu, Hawaii. Reston, Virigina: AIAA, 2011. doi: 10.2514/6.2011-3928
0
浏览量
0
下载量
0
CSCD
关联资源
相关文章
相关作者
相关机构
京公网安备11010802024621