S2046 (s2046-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 100,000 Max Cl/Cd: 55.89 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2046-il-100000-n5.txt Download as CSV file: xf-s2046-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4679 0.07716 0.07207 -0.0402 1.0000 0.0294
-8.500 -0.4760 0.07239 0.06738 -0.0422 1.0000 0.0293
-8.250 -0.4874 0.06695 0.06202 -0.0451 1.0000 0.0291
-8.000 -0.4984 0.05984 0.05491 -0.0517 1.0000 0.0287
-7.750 -0.5078 0.05385 0.04878 -0.0558 1.0000 0.0285
-7.500 -0.5125 0.04826 0.04294 -0.0585 1.0000 0.0284
-7.250 -0.5109 0.04301 0.03731 -0.0605 1.0000 0.0283
-7.000 -0.5027 0.03825 0.03206 -0.0618 1.0000 0.0283
-6.750 -0.4889 0.03416 0.02743 -0.0626 1.0000 0.0285
-6.500 -0.4712 0.03077 0.02348 -0.0629 1.0000 0.0290
-6.250 -0.4510 0.02815 0.02039 -0.0629 1.0000 0.0295
-6.000 -0.4306 0.02613 0.01816 -0.0626 1.0000 0.0303
-5.750 -0.4092 0.02467 0.01651 -0.0623 1.0000 0.0314
-5.500 -0.3873 0.02355 0.01522 -0.0618 1.0000 0.0334
-5.250 -0.3647 0.02247 0.01391 -0.0613 1.0000 0.0364
-5.000 -0.3404 0.02124 0.01249 -0.0610 0.9996 0.0390
-4.750 -0.3061 0.02015 0.01137 -0.0628 0.9957 0.0427
-4.500 -0.2717 0.01912 0.01015 -0.0643 0.9916 0.0489
-4.250 -0.2373 0.01836 0.00934 -0.0661 0.9871 0.0607
-4.000 -0.2013 0.01777 0.00882 -0.0682 0.9831 0.0780
-3.750 -0.1685 0.01742 0.00844 -0.0696 0.9773 0.1004
-3.500 -0.1335 0.01689 0.00795 -0.0714 0.9725 0.1197
-3.250 -0.0987 0.01643 0.00749 -0.0731 0.9678 0.1407
-3.000 -0.0657 0.01596 0.00710 -0.0744 0.9617 0.1661
-2.750 -0.0292 0.01544 0.00674 -0.0765 0.9572 0.2118
-2.500 0.0035 0.01481 0.00650 -0.0780 0.9512 0.3023
-2.250 0.0366 0.01430 0.00651 -0.0793 0.9454 0.4425
-2.000 0.0730 0.01414 0.00653 -0.0808 0.9408 0.5301
-1.750 0.1029 0.01407 0.00655 -0.0809 0.9326 0.5820
-1.500 0.1394 0.01400 0.00651 -0.0822 0.9274 0.6240
-1.250 0.1690 0.01395 0.00648 -0.0822 0.9183 0.6578
-1.000 0.2041 0.01386 0.00641 -0.0830 0.9116 0.6930
-0.750 0.2333 0.01376 0.00638 -0.0826 0.9017 0.7268
-0.500 0.2618 0.01365 0.00631 -0.0820 0.8916 0.7590
-0.250 0.2926 0.01349 0.00617 -0.0819 0.8825 0.7857
0.000 0.3209 0.01335 0.00604 -0.0814 0.8715 0.8069
0.250 0.3479 0.01321 0.00591 -0.0807 0.8595 0.8277
0.500 0.3750 0.01303 0.00577 -0.0799 0.8479 0.8507
0.750 0.4030 0.01283 0.00561 -0.0793 0.8363 0.8790
1.000 0.4362 0.01259 0.00542 -0.0798 0.8246 0.9241
1.250 0.4720 0.01248 0.00528 -0.0811 0.8112 1.0000
1.500 0.5023 0.01250 0.00524 -0.0814 0.7964 1.0000
1.750 0.5316 0.01254 0.00525 -0.0815 0.7800 1.0000
2.000 0.5604 0.01259 0.00526 -0.0814 0.7622 1.0000
2.250 0.5890 0.01265 0.00527 -0.0812 0.7433 1.0000
2.500 0.6177 0.01271 0.00528 -0.0810 0.7232 1.0000
2.750 0.6450 0.01281 0.00536 -0.0805 0.6996 1.0000
3.000 0.6723 0.01294 0.00542 -0.0801 0.6742 1.0000
3.250 0.6992 0.01309 0.00550 -0.0795 0.6456 1.0000
3.500 0.7256 0.01329 0.00563 -0.0789 0.6132 1.0000
3.750 0.7514 0.01355 0.00576 -0.0781 0.5772 1.0000
4.000 0.7763 0.01389 0.00593 -0.0773 0.5363 1.0000
4.250 0.8003 0.01432 0.00615 -0.0763 0.4926 1.0000
4.500 0.8237 0.01483 0.00647 -0.0754 0.4491 1.0000
4.750 0.8470 0.01537 0.00682 -0.0746 0.4091 1.0000
5.000 0.8703 0.01594 0.00722 -0.0738 0.3729 1.0000
5.250 0.8936 0.01650 0.00766 -0.0730 0.3385 1.0000
5.500 0.9167 0.01709 0.00817 -0.0723 0.3046 1.0000
5.750 0.9394 0.01771 0.00868 -0.0716 0.2705 1.0000
6.000 0.9620 0.01838 0.00924 -0.0708 0.2352 1.0000
6.250 0.9836 0.01916 0.00986 -0.0700 0.1970 1.0000
6.500 1.0048 0.02003 0.01059 -0.0692 0.1606 1.0000
6.750 1.0254 0.02100 0.01142 -0.0683 0.1330 1.0000
7.000 1.0453 0.02205 0.01233 -0.0673 0.1135 1.0000
7.500 1.0856 0.02405 0.01437 -0.0653 0.0907 1.0000
7.750 1.1046 0.02514 0.01551 -0.0642 0.0833 1.0000
8.000 1.1237 0.02620 0.01662 -0.0631 0.0764 1.0000
8.250 1.1419 0.02740 0.01788 -0.0619 0.0715 1.0000
8.500 1.1609 0.02857 0.01918 -0.0607 0.0672 1.0000
8.750 1.1785 0.02984 0.02047 -0.0595 0.0633 1.0000
9.000 1.1964 0.03123 0.02199 -0.0584 0.0597 1.0000
9.250 1.2150 0.03255 0.02350 -0.0572 0.0561 1.0000
9.500 1.2326 0.03400 0.02505 -0.0561 0.0534 1.0000
9.750 1.2487 0.03562 0.02669 -0.0550 0.0508 1.0000
10.000 1.2651 0.03732 0.02864 -0.0538 0.0480 1.0000
10.250 1.2804 0.03907 0.03066 -0.0524 0.0455 1.0000
10.500 1.2939 0.04086 0.03264 -0.0510 0.0433 1.0000
10.750 1.3053 0.04250 0.03439 -0.0496 0.0412 1.0000
11.000 1.3148 0.04476 0.03674 -0.0481 0.0393 1.0000
11.250 1.3183 0.04695 0.03934 -0.0457 0.0377 1.0000
11.500 1.3190 0.04944 0.04216 -0.0434 0.0363 1.0000
11.750 1.3169 0.05191 0.04491 -0.0412 0.0348 1.0000
12.000 1.3136 0.05434 0.04754 -0.0395 0.0336 1.0000
12.250 1.3107 0.05676 0.05012 -0.0381 0.0325 1.0000
12.500 1.3079 0.05939 0.05284 -0.0373 0.0315 1.0000
12.750 1.3024 0.06284 0.05640 -0.0367 0.0307 1.0000
13.000 1.2881 0.06739 0.06124 -0.0368 0.0304 1.0000
13.250 1.2702 0.07267 0.06683 -0.0379 0.0301 1.0000
13.500 1.2501 0.07872 0.07318 -0.0401 0.0299 1.0000
13.750 1.2280 0.08570 0.08043 -0.0435 0.0298 1.0000
14.000 1.2040 0.09374 0.08870 -0.0482 0.0299 1.0000
14.250 1.1784 0.10295 0.09812 -0.0542 0.0301 1.0000
14.500 1.1513 0.11349 0.10883 -0.0613 0.0303 1.0000
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Polar data table (+)
Polar graphs
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