S2046 (s2046-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 50,000 Max Cl/Cd: 38.66 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2046-il-50000.txt Download as CSV file: xf-s2046-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S2046
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3976 0.09321 0.08639 -0.0152 1.0000 0.2940
-7.250 -0.4068 0.09186 0.08517 -0.0140 1.0000 0.3070
-7.000 -0.3960 0.08841 0.08176 -0.0125 1.0000 0.3211
-6.750 -0.3888 0.08532 0.07872 -0.0109 1.0000 0.3348
-6.500 -0.3891 0.08287 0.07637 -0.0088 1.0000 0.3495
-6.250 -0.3895 0.08051 0.07411 -0.0066 1.0000 0.3641
-6.000 -0.4057 0.07947 0.07325 -0.0046 1.0000 0.3811
-5.750 -0.4322 0.06269 0.05629 -0.0403 1.0000 0.2040
-5.500 -0.4107 0.05026 0.04313 -0.0522 1.0000 0.1413
-5.250 -0.3866 0.04333 0.03525 -0.0578 1.0000 0.1293
-5.000 -0.3638 0.03929 0.03072 -0.0592 1.0000 0.1289
-4.750 -0.3427 0.03634 0.02763 -0.0595 1.0000 0.1349
-4.500 -0.3163 0.03329 0.02405 -0.0604 1.0000 0.1412
-4.250 -0.2905 0.03057 0.02100 -0.0607 1.0000 0.1504
-4.000 -0.2649 0.02844 0.01860 -0.0608 1.0000 0.1681
-3.750 -0.2390 0.02651 0.01645 -0.0607 1.0000 0.1921
-3.500 -0.2135 0.02490 0.01466 -0.0604 1.0000 0.2195
-3.250 -0.1895 0.02352 0.01333 -0.0597 1.0000 0.2496
-3.000 -0.1654 0.02225 0.01219 -0.0589 1.0000 0.2828
-2.750 -0.1403 0.02113 0.01129 -0.0584 1.0000 0.3352
-2.500 -0.1157 0.02003 0.01089 -0.0574 1.0000 0.4404
-2.250 -0.1059 0.01961 0.01143 -0.0518 1.0000 0.6226
-2.000 -0.1033 0.01962 0.01167 -0.0448 1.0000 0.7253
-1.750 -0.1017 0.01941 0.01153 -0.0381 1.0000 0.7978
-1.500 -0.1007 0.01888 0.01109 -0.0317 1.0000 0.8649
-1.250 -0.0752 0.01807 0.01029 -0.0311 1.0000 1.0000
-1.000 -0.0408 0.01816 0.00998 -0.0349 1.0000 1.0000
-0.750 -0.0085 0.01838 0.00986 -0.0378 1.0000 1.0000
-0.500 0.0215 0.01867 0.00987 -0.0399 1.0000 1.0000
-0.250 0.0494 0.01903 0.00997 -0.0416 1.0000 1.0000
0.000 0.0757 0.01944 0.01017 -0.0428 1.0000 1.0000
0.250 0.1005 0.01991 0.01046 -0.0437 1.0000 1.0000
0.500 0.1243 0.02043 0.01082 -0.0445 1.0000 1.0000
0.750 0.1470 0.02100 0.01126 -0.0451 1.0000 1.0000
1.000 0.1689 0.02164 0.01180 -0.0456 1.0000 1.0000
1.250 0.1898 0.02235 0.01242 -0.0461 1.0000 1.0000
1.500 0.2099 0.02313 0.01314 -0.0465 1.0000 1.0000
1.750 0.2396 0.02418 0.01415 -0.0489 0.9949 1.0000
2.000 0.3003 0.02563 0.01559 -0.0566 0.9727 1.0000
2.250 0.3561 0.02679 0.01678 -0.0630 0.9493 1.0000
2.500 0.4167 0.02779 0.01785 -0.0696 0.9266 1.0000
2.750 0.4668 0.02847 0.01863 -0.0740 0.9012 1.0000
3.000 0.5162 0.02897 0.01926 -0.0778 0.8753 1.0000
3.250 0.5674 0.02921 0.01967 -0.0814 0.8494 1.0000
3.500 0.6290 0.02892 0.01959 -0.0856 0.8250 1.0000
3.750 0.6787 0.02850 0.01937 -0.0875 0.7985 1.0000
4.250 0.7651 0.02724 0.01850 -0.0877 0.7426 1.0000
4.500 0.8048 0.02640 0.01781 -0.0867 0.7127 1.0000
4.750 0.8424 0.02547 0.01700 -0.0850 0.6806 1.0000
5.000 0.8713 0.02499 0.01656 -0.0825 0.6430 1.0000
5.250 0.9003 0.02447 0.01597 -0.0799 0.6029 1.0000
5.500 0.9253 0.02434 0.01575 -0.0772 0.5586 1.0000
5.750 0.9478 0.02456 0.01581 -0.0745 0.5111 1.0000
6.000 0.9695 0.02508 0.01605 -0.0720 0.4606 1.0000
6.250 0.9878 0.02602 0.01671 -0.0694 0.4046 1.0000
6.500 1.0052 0.02734 0.01767 -0.0669 0.3459 1.0000
6.750 1.0234 0.02904 0.01905 -0.0649 0.2932 1.0000
7.000 1.0440 0.03078 0.02044 -0.0633 0.2537 1.0000
7.250 1.0664 0.03269 0.02220 -0.0622 0.2251 1.0000
7.500 1.0882 0.03479 0.02449 -0.0611 0.2040 1.0000
7.750 1.1104 0.03681 0.02653 -0.0601 0.1868 1.0000
8.000 1.1330 0.03951 0.02952 -0.0592 0.1757 1.0000
8.250 1.1548 0.04221 0.03235 -0.0584 0.1661 1.0000
8.500 1.1746 0.04469 0.03500 -0.0574 0.1562 1.0000
8.750 1.1875 0.04841 0.03926 -0.0558 0.1513 1.0000
9.000 1.1961 0.05244 0.04385 -0.0541 0.1477 1.0000
9.250 1.2191 0.05553 0.04681 -0.0537 0.1409 1.0000
9.500 1.2138 0.06005 0.05204 -0.0513 0.1386 1.0000
9.750 1.2054 0.06501 0.05754 -0.0493 0.1374 1.0000
10.000 1.1926 0.07041 0.06335 -0.0477 0.1377 1.0000
10.250 1.1755 0.07598 0.06921 -0.0465 0.1385 1.0000
10.500 1.1564 0.08156 0.07500 -0.0456 0.1394 1.0000
10.750 1.1403 0.08716 0.08070 -0.0451 0.1404 1.0000
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Polar data table (+)
Polar graphs
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