NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 50,000 Max Cl/Cd: 23.42 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc0864c-il-50000.txt Download as CSV file: xf-rc0864c-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC08-64C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5751 0.12550 0.11817 0.0039 1.0000 0.1911
-9.500 -0.5625 0.12144 0.11410 0.0046 1.0000 0.2003
-9.250 -0.5911 0.12123 0.11406 -0.0002 1.0000 0.2053
-9.000 -0.5567 0.11447 0.10721 0.0034 1.0000 0.2164
-8.750 -0.5732 0.11229 0.10517 0.0005 1.0000 0.2232
-8.500 -0.5577 0.10813 0.10100 0.0019 1.0000 0.2359
-8.250 -0.5495 0.10406 0.09697 0.0023 1.0000 0.2456
-8.000 -0.5828 0.10329 0.09638 -0.0016 1.0000 0.2554
-7.750 -0.5658 0.09888 0.09198 0.0004 1.0000 0.2713
-7.500 -0.5560 0.09504 0.08818 0.0018 1.0000 0.2872
-7.250 -0.5571 0.09195 0.08515 0.0024 1.0000 0.3044
-7.000 -0.5691 0.08943 0.08275 0.0023 1.0000 0.3223
-6.750 -0.5361 0.08506 0.07835 0.0069 1.0000 0.3520
-6.250 -0.5246 0.07961 0.07303 0.0133 1.0000 0.4207
-6.000 -0.4992 0.07630 0.06973 0.0175 1.0000 0.4685
-4.750 -0.4964 0.04703 0.03826 -0.0196 1.0000 0.1394
-4.500 -0.4767 0.04302 0.03385 -0.0184 1.0000 0.1226
-4.250 -0.4562 0.04012 0.03012 -0.0166 1.0000 0.1095
-4.000 -0.4362 0.03678 0.02674 -0.0154 1.0000 0.1058
-3.750 -0.4143 0.03398 0.02351 -0.0139 1.0000 0.1000
-3.500 -0.3897 0.03201 0.02084 -0.0121 1.0000 0.0949
-3.250 -0.3655 0.02972 0.01830 -0.0110 1.0000 0.0935
-3.000 -0.3399 0.02778 0.01611 -0.0098 1.0000 0.0928
-2.750 -0.3131 0.02610 0.01421 -0.0088 1.0000 0.0935
-2.500 -0.2849 0.02464 0.01260 -0.0078 1.0000 0.0958
-2.250 -0.2570 0.02326 0.01127 -0.0072 1.0000 0.1041
-2.000 -0.1031 0.01732 0.00843 -0.0251 1.0000 1.0000
-1.750 -0.0898 0.01720 0.00796 -0.0226 1.0000 1.0000
-1.500 -0.0770 0.01711 0.00761 -0.0201 1.0000 1.0000
-1.250 -0.0646 0.01706 0.00733 -0.0176 1.0000 1.0000
-1.000 -0.0524 0.01703 0.00711 -0.0150 1.0000 1.0000
-0.750 -0.0402 0.01704 0.00694 -0.0125 1.0000 1.0000
-0.500 -0.0279 0.01708 0.00683 -0.0100 1.0000 1.0000
-0.250 -0.0153 0.01715 0.00676 -0.0076 1.0000 1.0000
0.000 -0.0023 0.01725 0.00675 -0.0053 1.0000 1.0000
0.250 0.0115 0.01739 0.00678 -0.0032 1.0000 1.0000
0.500 0.0260 0.01756 0.00687 -0.0013 1.0000 1.0000
0.750 0.0413 0.01777 0.00700 0.0004 1.0000 1.0000
1.000 0.0573 0.01801 0.00720 0.0019 1.0000 1.0000
1.250 0.0737 0.01830 0.00745 0.0032 1.0000 1.0000
1.500 0.0906 0.01862 0.00777 0.0044 1.0000 1.0000
1.750 0.1077 0.01899 0.00815 0.0054 1.0000 1.0000
2.000 0.1250 0.01941 0.00860 0.0063 1.0000 1.0000
2.250 0.1424 0.01989 0.00912 0.0070 1.0000 1.0000
2.500 0.1598 0.02041 0.00972 0.0077 1.0000 1.0000
2.750 0.1771 0.02100 0.01040 0.0081 1.0000 1.0000
3.000 0.1943 0.02166 0.01116 0.0085 1.0000 1.0000
3.250 0.2112 0.02239 0.01203 0.0088 1.0000 1.0000
3.500 0.2279 0.02321 0.01299 0.0089 1.0000 1.0000
3.750 0.2539 0.02424 0.01424 0.0070 0.9960 1.0000
4.000 0.5023 0.02145 0.00958 -0.0114 0.1688 1.0000
4.250 0.5190 0.02354 0.01120 -0.0093 0.1224 1.0000
4.500 0.5396 0.02500 0.01260 -0.0076 0.1057 1.0000
4.750 0.5639 0.02650 0.01414 -0.0063 0.0960 1.0000
5.000 0.5922 0.02813 0.01578 -0.0055 0.0906 1.0000
5.250 0.6231 0.03038 0.01794 -0.0051 0.0878 1.0000
5.500 0.6520 0.03253 0.02034 -0.0043 0.0870 1.0000
5.750 0.6788 0.03500 0.02312 -0.0033 0.0871 1.0000
6.000 0.7038 0.03789 0.02625 -0.0024 0.0879 1.0000
6.250 0.7253 0.04018 0.02930 -0.0003 0.0906 1.0000
6.500 0.7437 0.04345 0.03319 0.0015 0.0940 1.0000
6.750 0.7597 0.04694 0.03713 0.0032 0.0968 1.0000
7.000 0.7751 0.05069 0.04115 0.0045 0.0993 1.0000
7.250 0.7823 0.05489 0.04621 0.0066 0.1079 1.0000
7.500 0.7953 0.05952 0.05097 0.0075 0.1132 1.0000
7.750 0.8038 0.06539 0.05725 0.0082 0.1282 1.0000
8.500 0.6579 0.10068 0.09356 -0.0289 0.3573 1.0000
8.750 0.6684 0.10487 0.09773 -0.0288 0.3503 1.0000
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Polar data table (+)
Polar graphs
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