S2060 8% (s2060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.01 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2060-il-1000000-n5.txt Download as CSV file: xf-s2060-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2060 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5785 0.11212 0.11039 -0.0112 1.0000 0.0034
-11.750 -0.7104 0.07881 0.07706 -0.0281 1.0000 0.0032
-11.500 -0.8675 0.04106 0.03911 -0.0569 1.0000 0.0029
-11.250 -0.8788 0.03601 0.03381 -0.0584 1.0000 0.0029
-11.000 -0.8862 0.03157 0.02906 -0.0582 1.0000 0.0029
-10.750 -0.8821 0.02869 0.02592 -0.0574 1.0000 0.0030
-10.500 -0.8726 0.02651 0.02352 -0.0563 1.0000 0.0030
-10.250 -0.8607 0.02467 0.02146 -0.0551 1.0000 0.0031
-10.000 -0.8480 0.02289 0.01946 -0.0538 1.0000 0.0031
-9.750 -0.8337 0.02135 0.01772 -0.0525 1.0000 0.0032
-9.500 -0.8116 0.01998 0.01617 -0.0525 0.9993 0.0033
-9.250 -0.7839 0.01862 0.01460 -0.0535 0.9977 0.0033
-9.000 -0.7553 0.01750 0.01331 -0.0546 0.9960 0.0034
-8.750 -0.7257 0.01647 0.01213 -0.0557 0.9946 0.0035
-8.500 -0.6976 0.01560 0.01111 -0.0563 0.9926 0.0035
-8.250 -0.6691 0.01475 0.01011 -0.0570 0.9905 0.0036
-8.000 -0.6397 0.01395 0.00920 -0.0578 0.9885 0.0036
-7.750 -0.6102 0.01281 0.00788 -0.0588 0.9865 0.0039
-7.500 -0.5791 0.01208 0.00705 -0.0598 0.9850 0.0042
-7.250 -0.5473 0.01155 0.00645 -0.0610 0.9838 0.0045
-7.000 -0.5191 0.01107 0.00589 -0.0612 0.9804 0.0048
-6.750 -0.4901 0.01061 0.00536 -0.0616 0.9766 0.0051
-6.500 -0.4600 0.01019 0.00488 -0.0622 0.9735 0.0054
-6.250 -0.4289 0.00982 0.00444 -0.0630 0.9708 0.0058
-6.000 -0.4013 0.00951 0.00408 -0.0630 0.9656 0.0060
-5.750 -0.3724 0.00914 0.00364 -0.0633 0.9604 0.0068
-5.500 -0.3428 0.00880 0.00328 -0.0637 0.9558 0.0083
-5.250 -0.3156 0.00850 0.00297 -0.0636 0.9488 0.0117
-5.000 -0.2874 0.00819 0.00269 -0.0637 0.9424 0.0200
-4.750 -0.2602 0.00797 0.00248 -0.0636 0.9342 0.0253
-4.500 -0.2327 0.00778 0.00227 -0.0634 0.9264 0.0301
-4.250 -0.2054 0.00762 0.00209 -0.0633 0.9174 0.0340
-4.000 -0.1781 0.00747 0.00192 -0.0631 0.9088 0.0387
-3.750 -0.1510 0.00731 0.00177 -0.0629 0.8997 0.0466
-3.500 -0.1238 0.00715 0.00161 -0.0627 0.8895 0.0564
-3.250 -0.0966 0.00703 0.00147 -0.0625 0.8791 0.0645
-3.000 -0.0693 0.00692 0.00135 -0.0623 0.8684 0.0730
-2.750 -0.0422 0.00681 0.00123 -0.0621 0.8572 0.0863
-2.500 -0.0149 0.00669 0.00112 -0.0620 0.8454 0.1015
-2.250 0.0124 0.00658 0.00103 -0.0618 0.8332 0.1186
-2.000 0.0396 0.00648 0.00094 -0.0616 0.8198 0.1392
-1.750 0.0667 0.00634 0.00087 -0.0615 0.8051 0.1708
-1.500 0.0937 0.00622 0.00079 -0.0613 0.7890 0.2066
-1.250 0.1206 0.00611 0.00074 -0.0611 0.7717 0.2441
-1.000 0.1476 0.00603 0.00069 -0.0609 0.7523 0.2800
-0.750 0.1743 0.00591 0.00066 -0.0607 0.7313 0.3329
-0.500 0.2009 0.00578 0.00064 -0.0605 0.7084 0.3933
-0.250 0.2274 0.00569 0.00063 -0.0603 0.6842 0.4519
0.000 0.2537 0.00559 0.00064 -0.0600 0.6585 0.5218
0.250 0.2800 0.00550 0.00067 -0.0598 0.6315 0.5948
0.500 0.3063 0.00549 0.00071 -0.0594 0.6029 0.6481
0.750 0.3326 0.00554 0.00077 -0.0591 0.5735 0.6896
1.000 0.3589 0.00560 0.00083 -0.0588 0.5434 0.7241
1.250 0.3852 0.00569 0.00090 -0.0584 0.5130 0.7541
1.500 0.4113 0.00581 0.00098 -0.0580 0.4800 0.7828
1.750 0.4368 0.00594 0.00107 -0.0575 0.4441 0.8140
2.000 0.4616 0.00607 0.00119 -0.0568 0.4067 0.8495
2.250 0.4851 0.00631 0.00131 -0.0559 0.3553 0.8833
2.500 0.5071 0.00659 0.00145 -0.0547 0.2991 0.9198
2.750 0.5339 0.00683 0.00158 -0.0544 0.2531 0.9669
3.000 0.5667 0.00719 0.00174 -0.0557 0.2056 1.0000
3.250 0.5926 0.00750 0.00190 -0.0554 0.1720 1.0000
3.500 0.6181 0.00785 0.00209 -0.0551 0.1371 1.0000
3.750 0.6429 0.00830 0.00233 -0.0547 0.0914 1.0000
4.000 0.6683 0.00869 0.00257 -0.0543 0.0613 1.0000
4.250 0.6936 0.00909 0.00283 -0.0539 0.0352 1.0000
4.500 0.7188 0.00951 0.00313 -0.0535 0.0156 1.0000
4.750 0.7452 0.00975 0.00337 -0.0532 0.0128 1.0000
5.000 0.7716 0.00998 0.00363 -0.0530 0.0121 1.0000
5.250 0.7979 0.01023 0.00390 -0.0527 0.0115 1.0000
5.500 0.8239 0.01052 0.00420 -0.0524 0.0109 1.0000
5.750 0.8496 0.01084 0.00454 -0.0520 0.0101 1.0000
6.000 0.8749 0.01122 0.00495 -0.0516 0.0094 1.0000
6.250 0.8998 0.01166 0.00546 -0.0511 0.0089 1.0000
6.500 0.9241 0.01220 0.00606 -0.0504 0.0086 1.0000
6.750 0.9491 0.01259 0.00649 -0.0500 0.0085 1.0000
7.000 0.9737 0.01301 0.00696 -0.0495 0.0084 1.0000
7.250 0.9981 0.01346 0.00745 -0.0490 0.0082 1.0000
7.500 1.0223 0.01393 0.00799 -0.0484 0.0081 1.0000
7.750 1.0460 0.01444 0.00856 -0.0478 0.0079 1.0000
8.000 1.0694 0.01498 0.00916 -0.0471 0.0077 1.0000
8.250 1.0925 0.01555 0.00979 -0.0465 0.0074 1.0000
8.500 1.1154 0.01611 0.01042 -0.0458 0.0071 1.0000
8.750 1.1383 0.01665 0.01101 -0.0451 0.0068 1.0000
9.000 1.1605 0.01728 0.01172 -0.0443 0.0066 1.0000
9.250 1.1820 0.01796 0.01246 -0.0435 0.0064 1.0000
9.500 1.2034 0.01862 0.01319 -0.0426 0.0062 1.0000
9.750 1.2239 0.01936 0.01400 -0.0417 0.0060 1.0000
10.000 1.2435 0.02018 0.01490 -0.0406 0.0059 1.0000
10.250 1.2602 0.02132 0.01613 -0.0392 0.0056 1.0000
10.500 1.2716 0.02309 0.01807 -0.0372 0.0054 1.0000
10.750 1.2917 0.02365 0.01872 -0.0363 0.0053 1.0000
11.000 1.3093 0.02446 0.01963 -0.0350 0.0052 1.0000
11.250 1.3259 0.02530 0.02058 -0.0337 0.0051 1.0000
11.500 1.3398 0.02636 0.02175 -0.0320 0.0051 1.0000
11.750 1.3531 0.02733 0.02284 -0.0303 0.0049 1.0000
12.000 1.3606 0.02847 0.02411 -0.0277 0.0048 1.0000
12.250 1.3665 0.02962 0.02538 -0.0250 0.0047 1.0000
12.500 1.3705 0.03093 0.02682 -0.0224 0.0046 1.0000
12.750 1.3738 0.03234 0.02835 -0.0200 0.0045 1.0000
13.000 1.3769 0.03382 0.02994 -0.0179 0.0044 1.0000
13.250 1.3788 0.03550 0.03175 -0.0161 0.0043 1.0000
13.500 1.3826 0.03710 0.03345 -0.0147 0.0042 1.0000
13.750 1.3872 0.03872 0.03515 -0.0137 0.0040 1.0000
14.000 1.3847 0.04122 0.03779 -0.0129 0.0040 1.0000
14.250 1.3840 0.04373 0.04040 -0.0126 0.0039 1.0000
14.500 1.3852 0.04622 0.04297 -0.0127 0.0038 1.0000
14.750 1.3784 0.04997 0.04686 -0.0134 0.0038 1.0000
15.000 1.3756 0.05353 0.05052 -0.0147 0.0038 1.0000
15.250 1.3755 0.05695 0.05402 -0.0162 0.0037 1.0000
15.500 1.3464 0.06556 0.06287 -0.0207 0.0037 1.0000
15.750 1.3386 0.07114 0.06855 -0.0240 0.0037 1.0000
16.000 1.2840 0.08665 0.08438 -0.0336 0.0038 1.0000
16.250 1.2564 0.09749 0.09538 -0.0403 0.0038 1.0000
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Polar data table (+)
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