红外热像边界层转捩探测的飞行试验应用研究
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摘要
针对飞行试验层流测试,开展基于红外热像的边界层转捩探测技术应用研究。分析了高空飞行条件对红外测试的影响因素,包括光路布局、蒙皮表面处理工艺、蒙皮加热等,有针对性地提出红外测试方案。在此基础上,以某民用飞机为试验平台,开展飞行演示验证试验,飞行海拔高度范围5km至7km,马赫数范围0.5至0.65。进行了有/无蒙皮加热、有/无太阳等状态的机翼表面热图采集,对比分析蒙皮加热、太阳辐射等因素对红外转捩探测信噪比的影响特性,通过多个架次试验观测分析机翼前缘污染对转捩的影响特性。为消除由前缘污染物诱发湍流楔等因素导致转捩位置误判,提出了一种基于统计分析的机翼转捩位置判定方法,提高了转捩探测结果的可靠性。本文提供了三组真实飞行条件下的边界层转捩位置数据,雷诺数达到1.5×107。演示验证飞行试验结果表明,通过蒙皮内部加热方式可有效提高红外热图信噪比,利用固定转捩方法验证探测结果,使用本文方法测得的转捩位置偏差量不超过弦长0.5%。
The objective of this paper is to develop a boundary layer transition detect technique based on IR technique for laminar wing glove flight test.The main factors of flight environment affecting the technique were analyzed,including optical path,wing skin surface processing method,and heating etc.,and then the technique solutions for these influence factors were proposed.A flight test was designed to validate the IR transition detection method,and a classic civil aircraft was used as the test platform.The flight altitude was from 5 km to 7 km,and the flight Mach number was from 0.5 to 0.65.To analyze the effects of wing heating system and solar radiation on IR map,IR images acquisitions were carried out under conditions that the wing heating system was pulse-on and pulse-off.Furthermore,a shadow on the measurement region was built to utilize the azimuth between the airplane and sun.Several flights were carried out to show the effects of the leading edge pollutants on laminar boundary layer.A transition position determination method based on statistical analysis was proposed to avoid misjudgment of the transition position from turbulent wedges induced by leading edge pollutants.Standard circle roughness elements were used to validate IR measurement results.The test results show that the SNR can be increased significantly by wing skin surface heating.Three sets of wing boundary layer transition position under flight conditions are provided,and the Reynolds number is larger than 13 million.Compared with fixed transition,the error of transition position measured from IR image is less than 0.5%chord length.The transition detection method proposed in this paper is appropriate for the laminar wing glove flight test.
The objective of this paper is to develop a boundary layer transition detect technique based on IR technique for laminar wing glove flight test.The main factors of flight environment affecting the technique were analyzed,including optical path,wing skin surface processing method,and heating etc.,and then the technique solutions for these influence factors were proposed.A flight test was designed to validate the IR transition detection method,and a classic civil aircraft was used as the test platform.The flight altitude was from 5 km to 7 km,and the flight Mach number was from 0.5 to 0.65.To analyze the effects of wing heating system and solar radiation on IR map,IR images acquisitions were carried out under conditions that the wing heating system was pulse-on and pulse-off.Furthermore,a shadow on the measurement region was built to utilize the azimuth between the airplane and sun.Several flights were carried out to show the effects of the leading edge pollutants on laminar boundary layer.A transition position determination method based on statistical analysis was proposed to avoid misjudgment of the transition position from turbulent wedges induced by leading edge pollutants.Standard circle roughness elements were used to validate IR measurement results.The test results show that the SNR can be increased significantly by wing skin surface heating.Three sets of wing boundary layer transition position under flight conditions are provided,and the Reynolds number is larger than 13 million.Compared with fixed transition,the error of transition position measured from IR image is less than 0.5%chord length.The transition detection method proposed in this paper is appropriate for the laminar wing glove flight test.
引文
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[14]Wohlrath W,Echtle,Dick P,et al.Design and flight testevaluation of a laminar wing glove on a commuter aircraft[C]//ICAS-94-5.4.1,1994.
[15]SZEWCZYK M,SMUSZ R,GROOT K,et al.In-flight investigations of the unsteady behavior of the boundary layer with infrared thermography[J].Meas.Sci.Technol.28(2017)044002,DOI:10.1088/1361-6501/aa529c.
[16]CARPENTER A,SARIC W S,REED H L.Laminar flow control on a swept wing with distributed roughness[R].AIAA2008-7335.
[17]CRAWFORD B K,DUNCAN G T,WEST D E,et al.Laminar turbulent boundary layer transition imaging using IRthermography[J].Optics and Photonics Journal,2013,3:233-239,DOI:10.4236/opj.2013.33038.
[18]CRAWFORD B K,DUNCAN G T,WEST D E,et al.Robust automated processing of IR thermography for quantitative boundary layer transition measurements[J].Experiments in Fluids,2015,56:149,DOI:10.1007/s00348-015-2011-x.
[19]TUCKER A,REED H L,SARIC W S.Laminar flow control flight experiment design and execution[R].AIAA 2014-0909.
[20]ROBERTS M W,REED H L,SARIC W S.Computational evaluation and linear stability of a transonic laminar flow wing glove[J].Journal of Aircraft,2015,52(2):595-608.
[21]BANKS D.Detection and characterization of boundary layer transition in flight at supersonic conditions using infrared thermography[C]//13th International Symposium on Flow Visualization,Nice,France,2008.
[22]GARZON G A,MATISHECH J R,BANKS D W,et al.Supersonic NLF robustness flight testing:transition due to discrete roughness elements[R].AIAA 2014-2841.
[23]ASTARITA T,CARLOMAGNO G M.Infrared thermography in thermo fluid dynamics[M].Springer,Series:Experimental Fluid Mechanics 2012.
[24]BRASLOW A L.Review of the effect of distributed surface roughness on boundary layer transition[R].AGARD 254,1960.
[2]RUDOLPH A K,MARLYN Y A,LATUNIA M,et al.Flow disturbance characterization measurements in the national transonic facility[J].AIAA Juornal,2014,52(1):117-129.
[3]FANNING J A.In-flight measurements of freestream atmospheric turbulence intensities[D].Master thesis,Texas A&M University,2012.
[4]WADCOCK A J,YAMAUCHI G K,DRIVER D M.Skin friction measurements on a hovering full-scale tilt rotor[J].JAm Helicopter Soc,1999,44(4):312-319.
[5]SCHüLEIN E,ROSEMANN H,SCHABER S.Transition detection and skin friction measurements on rotating propeller blades[C]//28th AIAA aerodynamic measurement technology,ground testing and flght testing conference,New Orleans,Louisiana,USA.AIAA 2012-3202,doi:10.2514/6.2012-3202.
[6]YORITA D,ASAI K,KLEIN C,et al.Transition detection on rotating propeller blades by means of temperature-sensitive paint[C]//50th AIAA Aerospace Sciences Meeting,Nashville,Tennessee,USA,AIAA 2012-1187,doi:10.2514/6.2012-1187.
[7]SCHULTZ D L,JONES T V.Heat transfer measurements in short-duration hypersonic facilities[R].AGAR Dograph 165,AGARD-NATO,1973.
[8]ASTARITA T,CARDONE G,CARLOMAGNO G M,et al.A survey on infrared thermography for convective heat transfer measurements[J].Optics and Laser Technology,2000,32(7-8):593-610.
[9]LUCA L D,CARLOMAGNO G M,BURESTI G.Boundary layer diagnostics by means of an infrared scanning radiometer[J].Experiments in Fluids,1990,9(3):121-128.
[10]SANT Y L,MARCHAND M,MILLAN P,et al.An overview of infrared thermography techniques used in large wind tunnels[J].Aerospace Science and Technology,2002,6:355-366.
[11]KOWALEWSKI T,LIGRANI P,DREIZLER A,et al.Temperature and heat flx.In:Tropea C,Yarin A L,Foss J F(eds)Handbook of experimental flid mechanics[M].Springer,Berlin,2007:488-553.
[12]HORSTMANN K H,QUAST A,REDEKER G.Flight and windtunnel investigation on boundary layer transition at Reynolds numbers up to 107[C]//ICAS-88-3.7.1,1988.
[13]BRANDON J M,MANUEL G S,WRIGHT R E,et al.In flight flow visualization using infrared imaging[R].AIAA 1988-2111.
[14]Wohlrath W,Echtle,Dick P,et al.Design and flight testevaluation of a laminar wing glove on a commuter aircraft[C]//ICAS-94-5.4.1,1994.
[15]SZEWCZYK M,SMUSZ R,GROOT K,et al.In-flight investigations of the unsteady behavior of the boundary layer with infrared thermography[J].Meas.Sci.Technol.28(2017)044002,DOI:10.1088/1361-6501/aa529c.
[16]CARPENTER A,SARIC W S,REED H L.Laminar flow control on a swept wing with distributed roughness[R].AIAA2008-7335.
[17]CRAWFORD B K,DUNCAN G T,WEST D E,et al.Laminar turbulent boundary layer transition imaging using IRthermography[J].Optics and Photonics Journal,2013,3:233-239,DOI:10.4236/opj.2013.33038.
[18]CRAWFORD B K,DUNCAN G T,WEST D E,et al.Robust automated processing of IR thermography for quantitative boundary layer transition measurements[J].Experiments in Fluids,2015,56:149,DOI:10.1007/s00348-015-2011-x.
[19]TUCKER A,REED H L,SARIC W S.Laminar flow control flight experiment design and execution[R].AIAA 2014-0909.
[20]ROBERTS M W,REED H L,SARIC W S.Computational evaluation and linear stability of a transonic laminar flow wing glove[J].Journal of Aircraft,2015,52(2):595-608.
[21]BANKS D.Detection and characterization of boundary layer transition in flight at supersonic conditions using infrared thermography[C]//13th International Symposium on Flow Visualization,Nice,France,2008.
[22]GARZON G A,MATISHECH J R,BANKS D W,et al.Supersonic NLF robustness flight testing:transition due to discrete roughness elements[R].AIAA 2014-2841.
[23]ASTARITA T,CARLOMAGNO G M.Infrared thermography in thermo fluid dynamics[M].Springer,Series:Experimental Fluid Mechanics 2012.
[24]BRASLOW A L.Review of the effect of distributed surface roughness on boundary layer transition[R].AGARD 254,1960.