S3010-103-84 (s3010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 500,000 Max Cl/Cd: 89.19 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3010-il-500000-n5.txt Download as CSV file: xf-s3010-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4673 0.08388 0.08161 -0.0209 1.0000 0.0097
-9.250 -0.4746 0.07811 0.07588 -0.0241 1.0000 0.0096
-9.000 -0.4879 0.07135 0.06916 -0.0283 1.0000 0.0095
-8.750 -0.6080 0.03479 0.03182 -0.0558 0.9939 0.0089
-8.500 -0.5928 0.02824 0.02456 -0.0601 0.9639 0.0090
-8.250 -0.5729 0.02502 0.02087 -0.0612 0.9454 0.0092
-7.750 -0.5337 0.02124 0.01641 -0.0601 0.9141 0.0095
-7.500 -0.5123 0.01985 0.01473 -0.0593 0.9007 0.0097
-7.250 -0.4896 0.01868 0.01331 -0.0587 0.8884 0.0098
-7.000 -0.4659 0.01768 0.01209 -0.0581 0.8769 0.0100
-6.750 -0.4416 0.01684 0.01105 -0.0575 0.8657 0.0101
-6.500 -0.4165 0.01609 0.01013 -0.0571 0.8544 0.0103
-6.250 -0.3911 0.01537 0.00925 -0.0566 0.8435 0.0104
-6.000 -0.3665 0.01436 0.00812 -0.0562 0.8328 0.0107
-5.750 -0.3407 0.01377 0.00745 -0.0559 0.8220 0.0112
-5.500 -0.3144 0.01326 0.00685 -0.0556 0.8109 0.0116
-5.250 -0.2878 0.01279 0.00629 -0.0553 0.8002 0.0119
-5.000 -0.2613 0.01231 0.00571 -0.0550 0.7895 0.0123
-4.750 -0.2342 0.01186 0.00518 -0.0548 0.7784 0.0126
-4.500 -0.2071 0.01148 0.00470 -0.0545 0.7676 0.0130
-4.250 -0.1797 0.01114 0.00427 -0.0543 0.7569 0.0134
-4.000 -0.1523 0.01081 0.00385 -0.0541 0.7456 0.0138
-3.750 -0.1247 0.01048 0.00345 -0.0540 0.7347 0.0146
-3.500 -0.0970 0.01024 0.00313 -0.0538 0.7236 0.0155
-3.000 -0.0412 0.00984 0.00260 -0.0535 0.7008 0.0191
-2.750 -0.0133 0.00962 0.00236 -0.0534 0.6896 0.0253
-2.500 0.0144 0.00935 0.00215 -0.0533 0.6779 0.0496
-2.000 0.0699 0.00889 0.00185 -0.0533 0.6538 0.1167
-1.750 0.0976 0.00867 0.00174 -0.0533 0.6414 0.1625
-1.500 0.1253 0.00842 0.00165 -0.0533 0.6288 0.2202
-1.250 0.1529 0.00822 0.00158 -0.0532 0.6159 0.2782
-1.000 0.1805 0.00802 0.00152 -0.0532 0.6029 0.3431
-0.500 0.2356 0.00766 0.00147 -0.0531 0.5765 0.4769
-0.250 0.2632 0.00755 0.00146 -0.0530 0.5636 0.5308
0.000 0.2906 0.00744 0.00147 -0.0529 0.5505 0.5877
0.250 0.3178 0.00735 0.00149 -0.0526 0.5376 0.6458
0.500 0.3447 0.00727 0.00152 -0.0523 0.5242 0.7008
0.750 0.3711 0.00721 0.00156 -0.0518 0.5107 0.7538
1.000 0.3967 0.00716 0.00161 -0.0511 0.4971 0.8065
1.250 0.4211 0.00711 0.00167 -0.0500 0.4838 0.8617
1.500 0.4459 0.00708 0.00170 -0.0490 0.4711 0.9209
1.750 0.4835 0.00713 0.00172 -0.0509 0.4570 0.9785
2.000 0.5151 0.00725 0.00176 -0.0516 0.4436 1.0000
2.250 0.5427 0.00739 0.00182 -0.0515 0.4310 1.0000
2.500 0.5702 0.00754 0.00190 -0.0514 0.4180 1.0000
2.750 0.5976 0.00770 0.00198 -0.0513 0.4050 1.0000
3.000 0.6250 0.00787 0.00208 -0.0512 0.3912 1.0000
3.250 0.6524 0.00804 0.00219 -0.0511 0.3773 1.0000
3.500 0.6798 0.00822 0.00230 -0.0510 0.3631 1.0000
3.750 0.7071 0.00840 0.00243 -0.0509 0.3492 1.0000
4.000 0.7342 0.00860 0.00257 -0.0508 0.3350 1.0000
4.250 0.7613 0.00881 0.00272 -0.0507 0.3205 1.0000
4.500 0.7883 0.00903 0.00288 -0.0506 0.3060 1.0000
4.750 0.8151 0.00927 0.00307 -0.0504 0.2912 1.0000
5.000 0.8418 0.00951 0.00325 -0.0503 0.2771 1.0000
5.250 0.8683 0.00978 0.00346 -0.0501 0.2621 1.0000
5.500 0.8947 0.01005 0.00368 -0.0500 0.2477 1.0000
5.750 0.9210 0.01033 0.00392 -0.0498 0.2338 1.0000
6.000 0.9472 0.01062 0.00417 -0.0496 0.2209 1.0000
6.250 0.9732 0.01093 0.00443 -0.0494 0.2074 1.0000
6.500 0.9989 0.01126 0.00472 -0.0491 0.1945 1.0000
6.750 1.0245 0.01160 0.00502 -0.0489 0.1816 1.0000
7.000 1.0498 0.01196 0.00533 -0.0486 0.1695 1.0000
7.250 1.0748 0.01234 0.00568 -0.0483 0.1568 1.0000
7.500 1.0996 0.01273 0.00603 -0.0480 0.1444 1.0000
7.750 1.1243 0.01311 0.00639 -0.0476 0.1334 1.0000
8.000 1.1488 0.01352 0.00678 -0.0473 0.1230 1.0000
8.250 1.1728 0.01395 0.00720 -0.0469 0.1138 1.0000
8.500 1.1965 0.01440 0.00763 -0.0464 0.1052 1.0000
8.750 1.2202 0.01483 0.00806 -0.0459 0.0969 1.0000
9.000 1.2428 0.01535 0.00855 -0.0454 0.0873 1.0000
9.250 1.2649 0.01591 0.00909 -0.0448 0.0781 1.0000
9.500 1.2868 0.01644 0.00961 -0.0441 0.0702 1.0000
9.750 1.3083 0.01699 0.01016 -0.0434 0.0633 1.0000
10.000 1.3286 0.01762 0.01077 -0.0426 0.0565 1.0000
10.250 1.3490 0.01820 0.01138 -0.0418 0.0509 1.0000
10.500 1.3682 0.01884 0.01203 -0.0409 0.0458 1.0000
10.750 1.3866 0.01951 0.01271 -0.0398 0.0412 1.0000
11.000 1.4043 0.02018 0.01341 -0.0387 0.0376 1.0000
11.250 1.4207 0.02089 0.01415 -0.0374 0.0339 1.0000
11.500 1.4346 0.02166 0.01496 -0.0358 0.0307 1.0000
11.750 1.4459 0.02241 0.01577 -0.0338 0.0278 1.0000
12.000 1.4543 0.02336 0.01673 -0.0316 0.0247 1.0000
12.250 1.4634 0.02431 0.01775 -0.0297 0.0222 1.0000
12.500 1.4701 0.02550 0.01897 -0.0279 0.0194 1.0000
12.750 1.4762 0.02681 0.02033 -0.0262 0.0165 1.0000
13.000 1.4814 0.02828 0.02187 -0.0248 0.0142 1.0000
13.250 1.4847 0.03001 0.02366 -0.0235 0.0123 1.0000
13.500 1.4880 0.03187 0.02560 -0.0224 0.0108 1.0000
13.750 1.4893 0.03402 0.02783 -0.0216 0.0098 1.0000
14.000 1.4912 0.03625 0.03015 -0.0211 0.0091 1.0000
14.250 1.4923 0.03869 0.03270 -0.0208 0.0086 1.0000
14.500 1.4915 0.04145 0.03556 -0.0207 0.0082 1.0000
14.750 1.4891 0.04455 0.03877 -0.0210 0.0078 1.0000
15.000 1.4864 0.04782 0.04216 -0.0215 0.0077 1.0000
15.250 1.4798 0.05173 0.04619 -0.0224 0.0074 1.0000
15.500 1.4733 0.05580 0.05039 -0.0235 0.0072 1.0000
15.750 1.4675 0.05992 0.05464 -0.0248 0.0070 1.0000
16.000 1.4585 0.06472 0.05957 -0.0266 0.0069 1.0000
16.250 1.4492 0.06974 0.06473 -0.0286 0.0068 1.0000
16.500 1.4386 0.07516 0.07029 -0.0309 0.0067 1.0000
16.750 1.4275 0.08085 0.07613 -0.0335 0.0066 1.0000
17.000 1.4154 0.08685 0.08226 -0.0363 0.0065 1.0000
17.250 1.4014 0.09340 0.08896 -0.0395 0.0064 1.0000
17.500 1.3874 0.10012 0.09581 -0.0428 0.0064 1.0000
17.750 1.3723 0.10718 0.10301 -0.0464 0.0064 1.0000
18.000 1.3564 0.11460 0.11057 -0.0503 0.0063 1.0000
18.250 1.3410 0.12204 0.11815 -0.0543 0.0063 1.0000
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Polar data table (+)
Polar graphs
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