NASA-TN-D-1024-1962 Measured surface defects on typical transonic airplanes and analysis of their drag contribution《典型跨音速飞机上测量表面损坏及其阻力贡献的分析》.pdf

1、mro!Zb-m 491 = 0.0001213Awing 287.9CD,cwAsc _ 0.05856 = 0.0002032(CEkr)CW- Awing 287.9Values for scratches between 45 and 90 to flow (assumed to be perpen-dicular to flow) are as follows:Scratch Scratch hwidth, area, Asc , Bw _R win. 6q ft0.0003 12.39 94.6 0.997.001 9.94 182 3.32.002 6.36 364 6.64.0

2、03 12.71 546 9.97.009 _.30 910 16.61%o.o368.1226.8704.0014.9fcwo.134.44652._7.4518.4! 2_0.001338.0004012.O0O20O5.0001338.o0oo8o2c_0.00004920000492.o001745.ooo534.oo1196CDcw CDNAsc0.0001_2 0.00061.0001_2 .000_9.ooo%1 .00_1.0oo996 .oo6_00z_ .00634O.00222.0017100356801266.00782(c_)cw =l - 0“027_)8 = 0.0000972CD,CWAscAwing 287.9CDcwAscThe drag coefficient of scratches between 45 and 90 to the flow isI _ 0.01531 = 0.0000532CD,NAsc( D_Cw/N = Awing 287.9Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-