S3010-103-84 (s3010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 100,000 Max Cl/Cd: 50.15 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3010-il-100000.txt Download as CSV file: xf-s3010-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S3010-103-84
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3942 0.09905 0.09425 -0.0162 1.0000 0.1090
-8.500 -0.4026 0.09628 0.09158 -0.0203 1.0000 0.1136
-8.250 -0.4322 0.09386 0.08935 -0.0288 1.0000 0.1149
-8.000 -0.3897 0.08894 0.08433 -0.0213 1.0000 0.1195
-7.750 -0.3847 0.08598 0.08143 -0.0221 1.0000 0.1241
-7.500 -0.4122 0.08292 0.07853 -0.0315 1.0000 0.1291
-7.250 -0.4033 0.07868 0.07436 -0.0301 1.0000 0.1317
-7.000 -0.3887 0.07608 0.07179 -0.0273 1.0000 0.1356
-6.750 -0.4179 0.07169 0.06736 -0.0401 1.0000 0.1450
-6.500 -0.4015 0.06855 0.06439 -0.0348 1.0000 0.1468
-6.250 -0.3959 0.06648 0.06239 -0.0315 1.0000 0.1501
-5.750 -0.4173 0.06126 0.05717 -0.0314 1.0000 0.1622
-5.500 -0.4163 0.05936 0.05534 -0.0284 1.0000 0.1652
-5.250 -0.4107 0.04251 0.03700 -0.0402 1.0000 0.0852
-5.000 -0.3969 0.03641 0.03027 -0.0402 1.0000 0.0707
-4.750 -0.3809 0.03291 0.02638 -0.0398 1.0000 0.0669
-4.500 -0.3395 0.02849 0.02083 -0.0427 0.9947 0.0624
-4.250 -0.2972 0.02632 0.01845 -0.0462 0.9871 0.0653
-4.000 -0.2534 0.02444 0.01622 -0.0493 0.9793 0.0684
-3.750 -0.2069 0.02264 0.01406 -0.0525 0.9722 0.0715
-3.500 -0.1665 0.02101 0.01238 -0.0547 0.9631 0.0770
-3.250 -0.1224 0.01979 0.01125 -0.0578 0.9551 0.0941
-3.000 -0.0811 0.01818 0.00999 -0.0603 0.9462 0.1512
-2.750 -0.0432 0.01683 0.00949 -0.0628 0.9364 0.3082
-2.500 -0.0004 0.01586 0.00931 -0.0655 0.9289 0.4849
-2.250 0.0288 0.01535 0.00931 -0.0649 0.9169 0.6258
-2.000 0.0561 0.01504 0.00935 -0.0632 0.9056 0.7509
-1.750 0.0909 0.01477 0.00924 -0.0620 0.8976 0.8666
-1.500 0.1606 0.01450 0.00881 -0.0683 0.8892 0.9645
-1.250 0.2315 0.01412 0.00813 -0.0762 0.8817 1.0000
-1.000 0.2510 0.01415 0.00796 -0.0748 0.8661 1.0000
-0.750 0.2720 0.01419 0.00781 -0.0733 0.8516 1.0000
-0.500 0.2927 0.01427 0.00773 -0.0717 0.8367 1.0000
-0.250 0.3142 0.01436 0.00766 -0.0702 0.8220 1.0000
0.000 0.3366 0.01446 0.00761 -0.0687 0.8076 1.0000
0.250 0.3597 0.01455 0.00756 -0.0674 0.7932 1.0000
0.500 0.3833 0.01464 0.00753 -0.0661 0.7790 1.0000
0.750 0.4074 0.01473 0.00749 -0.0649 0.7650 1.0000
1.000 0.4319 0.01482 0.00746 -0.0638 0.7511 1.0000
1.250 0.4567 0.01490 0.00744 -0.0627 0.7373 1.0000
1.500 0.4819 0.01499 0.00742 -0.0616 0.7235 1.0000
1.750 0.5074 0.01508 0.00739 -0.0606 0.7099 1.0000
2.000 0.5330 0.01517 0.00737 -0.0597 0.6961 1.0000
2.250 0.5585 0.01531 0.00744 -0.0588 0.6812 1.0000
2.500 0.5841 0.01545 0.00750 -0.0580 0.6662 1.0000
2.750 0.6098 0.01560 0.00758 -0.0572 0.6511 1.0000
3.000 0.6357 0.01576 0.00768 -0.0564 0.6359 1.0000
3.250 0.6615 0.01594 0.00780 -0.0557 0.6206 1.0000
3.500 0.6874 0.01613 0.00792 -0.0550 0.6052 1.0000
3.750 0.7133 0.01633 0.00806 -0.0543 0.5897 1.0000
4.000 0.7393 0.01654 0.00824 -0.0536 0.5740 1.0000
4.250 0.7651 0.01677 0.00841 -0.0530 0.5581 1.0000
4.500 0.7909 0.01702 0.00859 -0.0523 0.5419 1.0000
4.750 0.8162 0.01730 0.00887 -0.0516 0.5247 1.0000
5.000 0.8414 0.01760 0.00917 -0.0510 0.5072 1.0000
5.250 0.8666 0.01790 0.00946 -0.0503 0.4896 1.0000
5.500 0.8917 0.01822 0.00975 -0.0496 0.4721 1.0000
5.750 0.9167 0.01855 0.01005 -0.0490 0.4544 1.0000
6.000 0.9417 0.01891 0.01036 -0.0483 0.4370 1.0000
6.250 0.9663 0.01931 0.01070 -0.0476 0.4192 1.0000
6.500 0.9900 0.01976 0.01119 -0.0469 0.4002 1.0000
6.750 1.0136 0.02021 0.01167 -0.0461 0.3814 1.0000
7.000 1.0372 0.02069 0.01211 -0.0454 0.3632 1.0000
7.250 1.0607 0.02120 0.01256 -0.0446 0.3453 1.0000
7.500 1.0831 0.02179 0.01318 -0.0438 0.3269 1.0000
7.750 1.1050 0.02241 0.01385 -0.0430 0.3083 1.0000
8.000 1.1267 0.02307 0.01450 -0.0421 0.2903 1.0000
8.250 1.1481 0.02379 0.01518 -0.0412 0.2731 1.0000
8.500 1.1692 0.02457 0.01593 -0.0404 0.2564 1.0000
8.750 1.1899 0.02546 0.01676 -0.0395 0.2404 1.0000
9.000 1.2091 0.02638 0.01773 -0.0385 0.2246 1.0000
9.250 1.2281 0.02738 0.01876 -0.0374 0.2097 1.0000
9.500 1.2467 0.02843 0.01984 -0.0364 0.1956 1.0000
9.750 1.2657 0.02958 0.02094 -0.0355 0.1826 1.0000
10.000 1.2820 0.03071 0.02221 -0.0342 0.1702 1.0000
10.250 1.2976 0.03204 0.02368 -0.0329 0.1589 1.0000
10.500 1.3135 0.03350 0.02526 -0.0317 0.1487 1.0000
10.750 1.3315 0.03497 0.02667 -0.0308 0.1393 1.0000
11.000 1.3444 0.03643 0.02831 -0.0293 0.1307 1.0000
11.250 1.3575 0.03826 0.03029 -0.0280 0.1230 1.0000
11.500 1.3744 0.03975 0.03170 -0.0271 0.1152 1.0000
11.750 1.3791 0.04185 0.03416 -0.0250 0.1091 1.0000
12.000 1.3977 0.04354 0.03565 -0.0246 0.1013 1.0000
12.250 1.3900 0.04542 0.03801 -0.0214 0.0970 1.0000
12.500 1.3913 0.04674 0.03937 -0.0192 0.0914 1.0000
12.750 1.3908 0.04904 0.04179 -0.0174 0.0866 1.0000
13.000 1.3801 0.05139 0.04442 -0.0152 0.0829 1.0000
13.250 1.3921 0.05326 0.04607 -0.0146 0.0766 1.0000
13.500 1.3743 0.05653 0.04975 -0.0132 0.0747 1.0000
13.750 1.3597 0.06008 0.05359 -0.0126 0.0720 1.0000
14.000 1.3524 0.06327 0.05692 -0.0126 0.0689 1.0000
14.250 1.3537 0.06649 0.06009 -0.0125 0.0649 1.0000
14.500 1.3317 0.07173 0.06567 -0.0137 0.0640 1.0000
14.750 1.3083 0.07769 0.07194 -0.0157 0.0633 1.0000
15.000 1.2832 0.08445 0.07898 -0.0187 0.0631 1.0000
15.250 1.2544 0.09233 0.08711 -0.0228 0.0632 1.0000
15.500 1.2235 0.10135 0.09636 -0.0280 0.0639 1.0000
15.750 1.1913 0.11151 0.10670 -0.0341 0.0649 1.0000
16.000 1.1581 0.12286 0.11818 -0.0411 0.0657 1.0000
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Polar data table (+)
Polar graphs
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