SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 100,000 Max Cl/Cd: 59.41 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6080-il-100000.txt Download as CSV file: xf-sd6080-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3398 0.10541 0.10058 -0.0300 1.0000 0.0777
-8.750 -0.3480 0.10410 0.09938 -0.0341 1.0000 0.0791
-8.500 -0.3592 0.10275 0.09816 -0.0381 1.0000 0.0795
-8.250 -0.3359 0.09605 0.09144 -0.0346 1.0000 0.0816
-8.000 -0.3242 0.09273 0.08814 -0.0333 1.0000 0.0845
-7.750 -0.3218 0.09010 0.08558 -0.0336 1.0000 0.0874
-7.500 -0.3268 0.08799 0.08358 -0.0340 1.0000 0.0900
-7.250 -0.3435 0.08689 0.08265 -0.0331 1.0000 0.0915
-7.000 -0.3654 0.08614 0.08204 -0.0325 1.0000 0.0924
-6.750 -0.3899 0.08546 0.08146 -0.0334 1.0000 0.0931
-6.500 -0.4079 0.08417 0.08015 -0.0366 1.0000 0.0936
-6.250 -0.4097 0.08042 0.07653 -0.0319 1.0000 0.0946
-6.000 -0.4104 0.07825 0.07444 -0.0264 1.0000 0.0963
-5.750 -0.4129 0.07633 0.07257 -0.0240 1.0000 0.0984
-5.500 -0.3719 0.06938 0.06535 -0.0424 0.9904 0.1089
-5.250 -0.3481 0.06597 0.06203 -0.0413 0.9855 0.1130
-5.000 -0.3131 0.06055 0.05638 -0.0515 0.9768 0.1247
-4.750 -0.2787 0.05638 0.05207 -0.0576 0.9704 0.1394
-4.500 -0.2497 0.05296 0.04857 -0.0612 0.9624 0.1547
-4.250 -0.2161 0.04950 0.04502 -0.0650 0.9563 0.1714
-4.000 -0.1830 0.04645 0.04171 -0.0700 0.9478 0.1975
-3.750 -0.1276 0.03910 0.03338 -0.0791 0.9427 0.1527
-3.500 -0.0804 0.02891 0.02143 -0.0807 0.9373 0.0630
-3.250 -0.0388 0.02630 0.01826 -0.0830 0.9321 0.0618
-3.000 -0.0018 0.02472 0.01620 -0.0843 0.9257 0.0650
-2.750 0.0349 0.02304 0.01442 -0.0859 0.9192 0.0718
-2.500 0.0808 0.02142 0.01273 -0.0888 0.9155 0.0852
-2.250 0.1074 0.02043 0.01184 -0.0885 0.9062 0.1204
-2.000 0.1462 0.01876 0.01098 -0.0907 0.9015 0.2646
-1.750 0.1640 0.01722 0.01099 -0.0887 0.8927 0.6195
-1.500 0.2266 0.01629 0.01042 -0.0935 0.8899 1.0000
-1.250 0.2592 0.01642 0.01023 -0.0944 0.8820 1.0000
-1.000 0.2913 0.01653 0.01007 -0.0950 0.8738 1.0000
-0.750 0.3179 0.01676 0.01008 -0.0949 0.8646 1.0000
-0.500 0.3517 0.01680 0.00991 -0.0956 0.8578 1.0000
-0.250 0.3754 0.01708 0.01004 -0.0949 0.8477 1.0000
0.000 0.4092 0.01707 0.00986 -0.0955 0.8418 1.0000
0.250 0.4316 0.01739 0.01007 -0.0946 0.8311 1.0000
0.500 0.4589 0.01756 0.01013 -0.0943 0.8229 1.0000
0.750 0.4867 0.01768 0.01015 -0.0939 0.8146 1.0000
1.000 0.5110 0.01796 0.01035 -0.0932 0.8049 1.0000
1.250 0.5413 0.01792 0.01023 -0.0930 0.7982 1.0000
1.500 0.5644 0.01824 0.01051 -0.0922 0.7875 1.0000
1.750 0.5912 0.01836 0.01059 -0.0916 0.7789 1.0000
2.000 0.6185 0.01842 0.01059 -0.0909 0.7701 1.0000
2.250 0.6428 0.01866 0.01082 -0.0901 0.7595 1.0000
2.500 0.6712 0.01861 0.01073 -0.0895 0.7516 1.0000
2.750 0.6966 0.01874 0.01087 -0.0886 0.7411 1.0000
3.000 0.7213 0.01893 0.01107 -0.0878 0.7300 1.0000
3.250 0.7483 0.01893 0.01106 -0.0870 0.7205 1.0000
3.500 0.7758 0.01885 0.01097 -0.0862 0.7106 1.0000
3.750 0.8005 0.01899 0.01117 -0.0853 0.6984 1.0000
4.000 0.8260 0.01906 0.01127 -0.0844 0.6863 1.0000
4.250 0.8523 0.01904 0.01128 -0.0835 0.6745 1.0000
4.500 0.8793 0.01896 0.01121 -0.0826 0.6626 1.0000
4.750 0.9068 0.01883 0.01112 -0.0817 0.6505 1.0000
5.000 0.9328 0.01879 0.01111 -0.0807 0.6366 1.0000
5.250 0.9587 0.01876 0.01112 -0.0797 0.6218 1.0000
5.500 0.9830 0.01882 0.01128 -0.0787 0.6050 1.0000
5.750 1.0076 0.01884 0.01138 -0.0776 0.5871 1.0000
6.000 1.0326 0.01879 0.01138 -0.0765 0.5685 1.0000
6.250 1.0585 0.01870 0.01128 -0.0754 0.5494 1.0000
6.500 1.0810 0.01879 0.01150 -0.0741 0.5256 1.0000
6.750 1.1041 0.01886 0.01160 -0.0727 0.5006 1.0000
7.000 1.1261 0.01902 0.01177 -0.0713 0.4726 1.0000
7.250 1.1466 0.01930 0.01207 -0.0698 0.4409 1.0000
7.500 1.1658 0.01974 0.01243 -0.0681 0.4069 1.0000
7.750 1.1831 0.02037 0.01300 -0.0663 0.3701 1.0000
8.000 1.1988 0.02119 0.01366 -0.0644 0.3338 1.0000
8.250 1.2131 0.02218 0.01455 -0.0625 0.2976 1.0000
8.500 1.2253 0.02328 0.01551 -0.0604 0.2632 1.0000
8.750 1.2351 0.02443 0.01656 -0.0582 0.2290 1.0000
9.000 1.2428 0.02562 0.01764 -0.0559 0.1962 1.0000
9.250 1.2489 0.02694 0.01887 -0.0534 0.1667 1.0000
9.500 1.2520 0.02846 0.02029 -0.0506 0.1392 1.0000
9.750 1.2496 0.03034 0.02202 -0.0473 0.1123 1.0000
10.000 1.2440 0.03279 0.02429 -0.0440 0.0875 1.0000
10.250 1.2405 0.03551 0.02679 -0.0411 0.0725 1.0000
10.500 1.2454 0.03775 0.02906 -0.0390 0.0629 1.0000
10.750 1.2546 0.03998 0.03141 -0.0373 0.0560 1.0000
11.000 1.2669 0.04226 0.03358 -0.0360 0.0510 1.0000
11.250 1.2895 0.04484 0.03637 -0.0350 0.0480 1.0000
11.500 1.3093 0.04755 0.03934 -0.0340 0.0457 1.0000
11.750 1.3250 0.05053 0.04258 -0.0330 0.0442 1.0000
12.000 1.3348 0.05365 0.04596 -0.0318 0.0430 1.0000
12.250 1.3412 0.05685 0.04935 -0.0306 0.0419 1.0000
12.500 1.3476 0.06118 0.05389 -0.0299 0.0407 1.0000
12.750 1.3399 0.06582 0.05880 -0.0286 0.0402 1.0000
13.000 1.3257 0.06942 0.06273 -0.0273 0.0400 1.0000
13.250 1.3108 0.07362 0.06721 -0.0267 0.0400 1.0000
13.500 1.2940 0.07825 0.07213 -0.0267 0.0400 1.0000
13.750 1.2761 0.08338 0.07750 -0.0273 0.0400 1.0000
14.000 1.2575 0.08903 0.08339 -0.0286 0.0401 1.0000
14.250 1.2387 0.09475 0.08936 -0.0306 0.0403 1.0000
14.500 1.2161 0.10069 0.09555 -0.0337 0.0406 1.0000
14.750 0.9630 0.11484 0.11069 -0.0400 0.0486 1.0000
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Polar data table (+)
Polar graphs
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