USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: USA 26 AIRFOIL (usa26-il) Reynolds number: 50,000 Max Cl/Cd: 35.29 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa26-il-50000-n5.txt Download as CSV file: xf-usa26-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 26 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3631 0.09793 0.09157 -0.0233 1.0000 0.1476
-7.250 -0.3889 0.09744 0.09124 -0.0231 1.0000 0.1511
-7.000 -0.4008 0.09519 0.08909 -0.0233 1.0000 0.1528
-6.750 -0.3881 0.09107 0.08500 -0.0199 1.0000 0.1562
-6.500 -0.3891 0.08853 0.08252 -0.0184 1.0000 0.1599
-6.000 -0.4072 0.08443 0.07849 -0.0199 1.0000 0.1685
-5.500 -0.3948 0.07126 0.06490 -0.0264 1.0000 0.0942
-5.250 -0.3888 0.06830 0.06192 -0.0250 1.0000 0.0929
-5.000 -0.3819 0.06516 0.05874 -0.0241 1.0000 0.0906
-4.750 -0.3687 0.05897 0.05203 -0.0271 1.0000 0.0809
-4.500 -0.3586 0.05621 0.04922 -0.0260 1.0000 0.0798
-4.250 -0.3321 0.05248 0.04524 -0.0284 0.9949 0.0783
-4.000 -0.2981 0.04832 0.04063 -0.0322 0.9869 0.0787
-3.750 -0.2641 0.04449 0.03621 -0.0353 0.9786 0.0799
-3.500 -0.2303 0.04135 0.03260 -0.0377 0.9701 0.0793
-3.250 -0.1934 0.03850 0.02923 -0.0403 0.9618 0.0789
-3.000 -0.1593 0.03613 0.02637 -0.0419 0.9516 0.0789
-2.750 -0.1241 0.03409 0.02382 -0.0434 0.9410 0.0792
-2.500 -0.0852 0.03244 0.02156 -0.0453 0.9304 0.0814
-2.250 -0.0463 0.03087 0.01991 -0.0476 0.9194 0.0850
-2.000 -0.0101 0.02960 0.01837 -0.0489 0.9062 0.0870
-1.750 0.0283 0.02840 0.01691 -0.0504 0.8928 0.0888
-1.500 0.0704 0.02734 0.01560 -0.0525 0.8796 0.0912
-1.250 0.1124 0.02642 0.01442 -0.0544 0.8658 0.0943
-1.000 0.1518 0.02551 0.01351 -0.0561 0.8515 0.0992
-0.750 0.1896 0.02472 0.01270 -0.0573 0.8364 0.1104
-0.500 0.2263 0.02392 0.01199 -0.0584 0.8206 0.1258
-0.250 0.2624 0.02308 0.01138 -0.0593 0.8039 0.1607
0.000 0.2972 0.02222 0.01102 -0.0600 0.7863 0.3073
0.500 0.4426 0.01990 0.00992 -0.0763 0.7433 1.0000
0.750 0.4759 0.01982 0.00952 -0.0767 0.7179 1.0000
1.000 0.5093 0.01979 0.00917 -0.0772 0.6937 1.0000
1.250 0.5375 0.01990 0.00901 -0.0768 0.6692 1.0000
1.500 0.5673 0.02004 0.00885 -0.0767 0.6479 1.0000
1.750 0.5932 0.02028 0.00886 -0.0761 0.6274 1.0000
2.000 0.6193 0.02056 0.00891 -0.0755 0.6097 1.0000
2.250 0.6450 0.02088 0.00904 -0.0749 0.5938 1.0000
2.500 0.6704 0.02123 0.00921 -0.0744 0.5793 1.0000
2.750 0.6960 0.02161 0.00943 -0.0738 0.5666 1.0000
3.000 0.7225 0.02200 0.00969 -0.0735 0.5553 1.0000
3.250 0.7470 0.02244 0.01007 -0.0729 0.5442 1.0000
3.500 0.7719 0.02290 0.01047 -0.0724 0.5341 1.0000
3.750 0.7992 0.02334 0.01084 -0.0723 0.5253 1.0000
4.000 0.8216 0.02387 0.01139 -0.0714 0.5159 1.0000
4.250 0.8482 0.02436 0.01183 -0.0712 0.5085 1.0000
4.500 0.8699 0.02494 0.01251 -0.0703 0.5003 1.0000
4.750 0.8967 0.02546 0.01298 -0.0701 0.4937 1.0000
5.000 0.9161 0.02610 0.01376 -0.0687 0.4857 1.0000
5.250 0.9413 0.02667 0.01434 -0.0683 0.4794 1.0000
5.500 0.9609 0.02738 0.01521 -0.0671 0.4725 1.0000
5.750 0.9834 0.02798 0.01587 -0.0662 0.4653 1.0000
6.000 1.0020 0.02863 0.01663 -0.0647 0.4568 1.0000
6.250 1.0249 0.02909 0.01713 -0.0637 0.4479 1.0000
6.500 1.0395 0.02971 0.01790 -0.0615 0.4373 1.0000
6.750 1.0583 0.03021 0.01847 -0.0599 0.4276 1.0000
7.000 1.0779 0.03073 0.01909 -0.0584 0.4187 1.0000
7.250 1.0938 0.03147 0.02004 -0.0566 0.4106 1.0000
7.500 1.1150 0.03198 0.02065 -0.0554 0.4027 1.0000
7.750 1.1283 0.03280 0.02168 -0.0532 0.3940 1.0000
8.000 1.1514 0.03325 0.02221 -0.0523 0.3864 1.0000
8.250 1.1612 0.03419 0.02343 -0.0496 0.3772 1.0000
8.500 1.1811 0.03474 0.02412 -0.0482 0.3690 1.0000
8.750 1.1925 0.03563 0.02526 -0.0458 0.3599 1.0000
9.000 1.2069 0.03641 0.02624 -0.0438 0.3511 1.0000
9.250 1.2244 0.03661 0.02650 -0.0418 0.3398 1.0000
9.500 1.2303 0.03700 0.02703 -0.0384 0.3259 1.0000
9.750 1.2326 0.03747 0.02764 -0.0345 0.3116 1.0000
10.000 1.2331 0.03818 0.02851 -0.0306 0.2985 1.0000
10.250 1.2337 0.03905 0.02961 -0.0268 0.2877 1.0000
10.500 1.2366 0.03980 0.03048 -0.0234 0.2774 1.0000
10.750 1.2337 0.04083 0.03167 -0.0196 0.2658 1.0000
11.000 1.2265 0.04236 0.03341 -0.0160 0.2536 1.0000
11.250 1.2200 0.04409 0.03532 -0.0130 0.2419 1.0000
11.500 1.2164 0.04593 0.03733 -0.0107 0.2322 1.0000
11.750 1.2091 0.04810 0.03963 -0.0086 0.2198 1.0000
12.000 1.1973 0.05086 0.04247 -0.0070 0.2043 1.0000
12.250 1.1846 0.05400 0.04556 -0.0061 0.1865 1.0000
12.500 1.1716 0.05760 0.04904 -0.0057 0.1699 1.0000
12.750 1.1556 0.06200 0.05334 -0.0061 0.1537 1.0000
13.000 1.1425 0.06668 0.05813 -0.0069 0.1422 1.0000
13.250 1.1280 0.07179 0.06332 -0.0082 0.1290 1.0000
13.500 1.1135 0.07709 0.06872 -0.0096 0.1143 1.0000
13.750 1.1008 0.08225 0.07397 -0.0110 0.0997 1.0000
14.000 1.0876 0.08754 0.07924 -0.0125 0.0817 1.0000
14.250 1.0749 0.09271 0.08429 -0.0141 0.0707 1.0000
14.500 1.0611 0.09820 0.08960 -0.0158 0.0632 1.0000
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Polar data table (+)
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