S3010-103-84 (s3010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3010-il-1000000.txt Download as CSV file: xf-s3010-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4445 0.08466 0.08308 -0.0214 1.0000 0.0144
-9.000 -0.4441 0.08071 0.07915 -0.0236 1.0000 0.0147
-8.750 -0.4478 0.07588 0.07434 -0.0264 1.0000 0.0147
-8.500 -0.4522 0.07126 0.06976 -0.0293 1.0000 0.0149
-8.250 -0.4644 0.06582 0.06437 -0.0331 1.0000 0.0151
-8.000 -0.4846 0.05204 0.05052 -0.0483 1.0000 0.0150
-7.750 -0.4802 0.03780 0.03573 -0.0608 0.9569 0.0157
-7.500 -0.4739 0.03343 0.03065 -0.0605 0.9293 0.0171
-7.250 -0.4883 0.01976 0.01578 -0.0593 0.9084 0.0122
-7.000 -0.4688 0.01695 0.01250 -0.0583 0.8960 0.0117
-6.750 -0.4451 0.01565 0.01097 -0.0576 0.8845 0.0119
-6.500 -0.4201 0.01464 0.00979 -0.0572 0.8735 0.0121
-6.250 -0.3946 0.01384 0.00884 -0.0567 0.8630 0.0124
-6.000 -0.3687 0.01315 0.00801 -0.0563 0.8523 0.0127
-5.750 -0.3423 0.01248 0.00723 -0.0559 0.8418 0.0129
-5.500 -0.3156 0.01195 0.00659 -0.0556 0.8316 0.0131
-5.250 -0.2889 0.01144 0.00597 -0.0553 0.8212 0.0132
-5.000 -0.2616 0.01103 0.00549 -0.0551 0.8108 0.0134
-4.750 -0.2348 0.01043 0.00479 -0.0548 0.8007 0.0136
-4.500 -0.2082 0.00976 0.00402 -0.0545 0.7901 0.0141
-4.250 -0.1807 0.00938 0.00360 -0.0544 0.7796 0.0148
-4.000 -0.1529 0.00910 0.00326 -0.0543 0.7693 0.0155
-3.500 -0.0969 0.00861 0.00263 -0.0540 0.7476 0.0169
-3.250 -0.0689 0.00833 0.00228 -0.0538 0.7368 0.0183
-3.000 -0.0407 0.00814 0.00204 -0.0537 0.7258 0.0201
-2.750 -0.0125 0.00795 0.00182 -0.0536 0.7141 0.0247
-2.500 0.0153 0.00755 0.00159 -0.0536 0.7027 0.0688
-2.250 0.0432 0.00729 0.00146 -0.0536 0.6911 0.1140
-2.000 0.0712 0.00708 0.00135 -0.0536 0.6790 0.1582
-1.750 0.0992 0.00688 0.00126 -0.0536 0.6666 0.2052
-1.500 0.1272 0.00667 0.00119 -0.0537 0.6542 0.2615
-1.250 0.1552 0.00648 0.00114 -0.0537 0.6418 0.3198
-1.000 0.1830 0.00624 0.00110 -0.0537 0.6294 0.4007
-0.750 0.2108 0.00605 0.00108 -0.0537 0.6165 0.4744
-0.500 0.2385 0.00589 0.00107 -0.0536 0.6034 0.5452
-0.250 0.2661 0.00573 0.00108 -0.0535 0.5898 0.6192
0.250 0.3211 0.00554 0.00112 -0.0531 0.5624 0.7330
0.500 0.3480 0.00546 0.00115 -0.0527 0.5488 0.7896
0.750 0.3738 0.00539 0.00119 -0.0521 0.5357 0.8470
1.000 0.3980 0.00533 0.00123 -0.0509 0.5229 0.9024
1.250 0.4249 0.00531 0.00125 -0.0503 0.5096 0.9593
1.500 0.4654 0.00538 0.00125 -0.0530 0.4949 1.0000
2.000 0.5211 0.00560 0.00133 -0.0528 0.4681 1.0000
2.250 0.5490 0.00572 0.00138 -0.0528 0.4545 1.0000
2.500 0.5769 0.00585 0.00144 -0.0527 0.4411 1.0000
2.750 0.6048 0.00598 0.00151 -0.0527 0.4275 1.0000
3.000 0.6326 0.00612 0.00158 -0.0526 0.4140 1.0000
3.250 0.6604 0.00627 0.00167 -0.0526 0.4006 1.0000
3.500 0.6881 0.00642 0.00176 -0.0525 0.3869 1.0000
3.750 0.7157 0.00658 0.00186 -0.0525 0.3732 1.0000
4.000 0.7433 0.00675 0.00198 -0.0524 0.3586 1.0000
4.250 0.7708 0.00693 0.00209 -0.0524 0.3442 1.0000
4.500 0.7983 0.00712 0.00222 -0.0523 0.3291 1.0000
4.750 0.8256 0.00732 0.00236 -0.0522 0.3142 1.0000
5.000 0.8528 0.00753 0.00251 -0.0521 0.2990 1.0000
5.250 0.8799 0.00775 0.00267 -0.0520 0.2837 1.0000
5.500 0.9069 0.00799 0.00285 -0.0519 0.2688 1.0000
5.750 0.9337 0.00823 0.00304 -0.0518 0.2535 1.0000
6.000 0.9604 0.00849 0.00324 -0.0517 0.2390 1.0000
6.250 0.9869 0.00876 0.00345 -0.0515 0.2242 1.0000
6.500 1.0133 0.00904 0.00368 -0.0514 0.2097 1.0000
6.750 1.0394 0.00934 0.00392 -0.0512 0.1950 1.0000
7.000 1.0654 0.00966 0.00417 -0.0510 0.1816 1.0000
7.250 1.0912 0.00998 0.00445 -0.0508 0.1685 1.0000
7.500 1.1169 0.01031 0.00473 -0.0506 0.1560 1.0000
7.750 1.1426 0.01062 0.00501 -0.0503 0.1451 1.0000
8.000 1.1680 0.01096 0.00532 -0.0501 0.1344 1.0000
8.250 1.1929 0.01135 0.00566 -0.0497 0.1224 1.0000
8.500 1.2174 0.01176 0.00602 -0.0494 0.1106 1.0000
8.750 1.2415 0.01219 0.00640 -0.0490 0.0997 1.0000
9.000 1.2654 0.01264 0.00680 -0.0486 0.0897 1.0000
9.250 1.2895 0.01303 0.00718 -0.0481 0.0822 1.0000
9.500 1.3129 0.01349 0.00761 -0.0477 0.0738 1.0000
9.750 1.3354 0.01401 0.00809 -0.0471 0.0652 1.0000
10.000 1.3581 0.01449 0.00855 -0.0465 0.0586 1.0000
10.250 1.3805 0.01497 0.00903 -0.0459 0.0530 1.0000
10.500 1.4017 0.01553 0.00957 -0.0452 0.0474 1.0000
10.750 1.4235 0.01601 0.01007 -0.0445 0.0434 1.0000
11.000 1.4435 0.01661 0.01066 -0.0436 0.0390 1.0000
11.250 1.4640 0.01713 0.01120 -0.0428 0.0356 1.0000
11.500 1.4823 0.01779 0.01185 -0.0417 0.0317 1.0000
11.750 1.5009 0.01837 0.01247 -0.0406 0.0285 1.0000
12.000 1.5161 0.01915 0.01323 -0.0392 0.0242 1.0000
12.250 1.5294 0.01996 0.01404 -0.0375 0.0199 1.0000
12.500 1.5355 0.02092 0.01500 -0.0346 0.0153 1.0000
13.000 1.5450 0.02310 0.01724 -0.0295 0.0106 1.0000
13.250 1.5493 0.02438 0.01858 -0.0273 0.0097 1.0000
13.500 1.5540 0.02576 0.02004 -0.0255 0.0091 1.0000
13.750 1.5594 0.02720 0.02156 -0.0241 0.0085 1.0000
14.000 1.5643 0.02877 0.02322 -0.0228 0.0083 1.0000
14.250 1.5655 0.03078 0.02530 -0.0217 0.0078 1.0000
14.500 1.5674 0.03285 0.02746 -0.0209 0.0076 1.0000
14.750 1.5637 0.03562 0.03034 -0.0202 0.0073 1.0000
15.000 1.5577 0.03882 0.03366 -0.0200 0.0070 1.0000
15.250 1.5571 0.04160 0.03655 -0.0201 0.0069 1.0000
15.500 1.5556 0.04462 0.03967 -0.0204 0.0068 1.0000
15.750 1.5509 0.04817 0.04334 -0.0210 0.0068 1.0000
16.000 1.5444 0.05212 0.04741 -0.0220 0.0067 1.0000
16.250 1.5378 0.05624 0.05165 -0.0232 0.0065 1.0000
16.500 1.5270 0.06116 0.05669 -0.0249 0.0065 1.0000
16.750 1.5177 0.06610 0.06175 -0.0268 0.0065 1.0000
17.000 1.5059 0.07161 0.06739 -0.0292 0.0064 1.0000
17.250 1.4919 0.07769 0.07360 -0.0319 0.0064 1.0000
17.500 1.4761 0.08427 0.08032 -0.0350 0.0063 1.0000
17.750 1.4614 0.09086 0.08703 -0.0382 0.0063 1.0000
18.000 1.4441 0.09812 0.09442 -0.0418 0.0063 1.0000
18.250 1.4267 0.10556 0.10199 -0.0456 0.0063 1.0000
18.500 1.4087 0.11332 0.10988 -0.0498 0.0062 1.0000
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Polar data table (+)
Polar graphs
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