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风洞实验数据的误差及其计算方法 被引量:4

THE ERROR OF WIND TUNNEL TESTING DATA AND ITS CALCULATING METHODS
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摘要 本文首先简述了研究风洞实验数据误差的意义,然后给出系统误差、随机误差、粗差及不确定度的定义,在讲述了单点测量标准差、多点测量标准差及随机不确定度计算方法之后,介绍了系统误差的判别和风洞实验数据误差的合成,最后给出了风洞气流参数、压力系数及力系数随机误差的计算公式。 The significance of studing the error of wind tunnel testing data is reviewed briefly.Definitions of systematic error,randomerror,parasitic error and uncertainty are presented.After explaining thestandard deviations of single-point and multi-point measurements,and thecalcuation methods of random uncertainty,a method to distinguish thesystematic error and the composite method for wind Tunnel testing errorare introduced.Finally,the formula for calculating random error of windfunnel flow param-eters,aerodynamic pressure and force coefficients aregiven.
作者 恽起麟
出处 《气动实验与测量控制》 CSCD 1993年第4期67-77,共11页
关键词 风洞实验 数据处理 数据误差 wind tunnel testing data processing data error
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  • 1戴荣尧,王群,梁在潮,李谋恒.探讨通过水流模型试验进行高速列车空气动力学研究的可行性[J].中国铁道科学,1993,14(3):50-57. 被引量:6
  • 2恽起麟.对风洞实验数据精准度的要求[J].气动实验与测量控制,1994,8(1):66-72. 被引量:5
  • 3Keener E R,Jordan C H.Wing pressure distribution over the liftrange of the convair XF-92A delta-wing airplane at subsonic and tran-sonic speeds.NACA RM H55G07,November 1955.
  • 4Pyle J S.Flight-measured wing surface pressures and loads for the X-15 airplane at mach numbers from 1.2 to 6.0.NASA TN D-2602,January 1965.
  • 5Montoya L C,Banner R D.F-8 supercritical wing flight pressure,boundary-layer,and wake measurements and comparisons with thewind tunnel data.NASA TM X-3544,June 1977.
  • 6Moes T R,Meyer,Jr R R.In-flight Investigation of shuttle tile pres-sure orifice installations.NASA TM-4219,September 1990.
  • 7Powers S G,Webb L D.Flight wing surface pressure and boudary-layer data report from the F-111 smooth variable-camber supercriti-cal mission adaptive wing.NASA TM-4789,June 1997.
  • 8Landers S F,Saltzman J A.F-16XL wing pressure distributions andshock fence results from Mach 1.4 to Mach 2.0.NASA/TM-97-206219,1997.
  • 9Davis M,Saltzman J.In-flight wing pressure distributions for theNASA F/A-18A high alpha research vehicle.NASA/TP-2000-209018,2000.
  • 10原正庭.亚音速飞机压力分布测量[J].航空学报,1998,19(4):486-488. 被引量:6

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