Sidewall Mach Number Distributions for the NASA Langley Transonic Dynamics Tunnel
Sidewall Mach Number Distributions for the NASA Langley Transonic Dynamics Tunnel
复制标题
NASA 兰利跨音速动力学隧道的侧壁马赫数分布
DOI：
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发表时间：
2001
期刊：
影响因子：
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通讯作者：
J. A. Rivera
中科院分区：
文献类型：
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作者：
J. Florance;J. A. Rivera
摘要由于重气体试验介质由R-12转换为R-134a，对TDT进行了重新校准。测试的目的是确定自由流马赫数和测量的测试段马赫数之间的关系，并量化任何必要的修正。其他测试包括沿测试段壁、测试段中心线的压力分布测量，在某些隧道站，通过一个耙装置，以及在隧道沉降室。还进行了壁面边界层、湍流和流度测量。本文讨论了侧壁马赫数分布的确定。，RA'7襟翼设置，计数襟翼计划配置数马赫数压力，动压力，温度，距离隧道收缩原点下游的距离，襟翼宽度，in。距离隧道中心线的横向尺寸（使用右手定则为正），距离隧道中心线的垂直尺寸（向上为正），入口后皮瓣角度（当皮瓣表面偏离隧道中心线时为正），度。差分算子比热比下标：局部
ABSTRACTThe TDT was recalibrated due to the conversion of theheavy gas test medium from R-12 to R-134a. The objectives ofthe tests were to determine the relationship between the free-stream Mach number and the measured test section Machnumber, and to quantify any necessary corrections. Other testsincluded the measurement of pressure distributions along thetest-section walls, test-section centerline, at certain tunnelstations via a rake apparatus, and in the tunnel settlingchamber. Wall boundary layer, turbulence, and flowangularity measurements were also performed. This paperdiscusses the determination of sidewall Mach numberdistributions.SYMBOLSMPqTXYsYZo?,RA'7flap setting, countsflap schedule configuration numberMach Numberpressure, psfdynamic pressure, psftemperature, °Fdistance downstream from origin of tunnel contraction, ftslot width, in.lateral dimension from tunnel centerline (positive using right-hand rule), ftvertical dimension from tunnel centerline (positive upward), ftre-entry flap angle (positive when flap surface is divergent from tunnel centerline),deg.difference operatorratio of specific heatsSubscripts:local