S2046 (s2046-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 200,000 Max Cl/Cd: 77.9 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2046-il-200000.txt Download as CSV file: xf-s2046-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4188 0.09752 0.09380 -0.0278 1.0000 0.0554
-9.000 -0.4183 0.09404 0.09036 -0.0295 1.0000 0.0571
-8.750 -0.4271 0.08998 0.08637 -0.0339 1.0000 0.0596
-8.500 -0.3609 0.07403 0.07073 -0.0378 1.0000 0.0622
-8.250 -0.3539 0.07128 0.06799 -0.0364 1.0000 0.0633
-8.000 -0.3537 0.06817 0.06493 -0.0360 1.0000 0.0643
-7.750 -0.4625 0.07197 0.06867 -0.0441 1.0000 0.0620
-7.500 -0.4573 0.07019 0.06692 -0.0414 1.0000 0.0629
-7.250 -0.4583 0.06685 0.06363 -0.0425 1.0000 0.0637
-7.000 -0.4608 0.06330 0.06008 -0.0439 1.0000 0.0647
-6.750 -0.4637 0.05959 0.05634 -0.0452 1.0000 0.0659
-6.500 -0.4646 0.05558 0.05225 -0.0468 1.0000 0.0677
-6.250 -0.4661 0.03232 0.02727 -0.0593 1.0000 0.0368
-6.000 -0.4467 0.02873 0.02320 -0.0599 1.0000 0.0368
-5.750 -0.4248 0.02629 0.02029 -0.0600 1.0000 0.0375
-5.500 -0.4013 0.02365 0.01723 -0.0601 1.0000 0.0376
-5.250 -0.3769 0.02159 0.01480 -0.0601 1.0000 0.0377
-5.000 -0.3523 0.02013 0.01306 -0.0598 1.0000 0.0382
-4.750 -0.3260 0.01794 0.01068 -0.0600 1.0000 0.0398
-4.500 -0.2926 0.01693 0.00963 -0.0614 0.9978 0.0427
-4.250 -0.2542 0.01618 0.00877 -0.0636 0.9945 0.0477
-4.000 -0.2174 0.01533 0.00795 -0.0657 0.9907 0.0584
-3.750 -0.1792 0.01449 0.00717 -0.0680 0.9867 0.0832
-3.500 -0.1391 0.01410 0.00679 -0.0708 0.9833 0.1052
-3.250 -0.1040 0.01389 0.00660 -0.0726 0.9774 0.1294
-3.000 -0.0652 0.01343 0.00627 -0.0751 0.9729 0.1573
-2.750 -0.0238 0.01285 0.00590 -0.0782 0.9696 0.2033
-2.500 0.0089 0.01193 0.00566 -0.0799 0.9631 0.3439
-2.250 0.0476 0.01146 0.00576 -0.0822 0.9583 0.5173
-2.000 0.0851 0.01136 0.00578 -0.0839 0.9524 0.5825
-1.750 0.1230 0.01126 0.00575 -0.0855 0.9456 0.6264
-1.500 0.1684 0.01114 0.00564 -0.0885 0.9419 0.6637
-1.250 0.2010 0.01104 0.00558 -0.0889 0.9332 0.6897
-1.000 0.2412 0.01086 0.00543 -0.0908 0.9283 0.7143
-0.750 0.2725 0.01075 0.00534 -0.0910 0.9195 0.7365
-0.500 0.3079 0.01055 0.00519 -0.0917 0.9136 0.7598
-0.250 0.3346 0.01044 0.00514 -0.0908 0.9037 0.7851
0.000 0.3631 0.01028 0.00503 -0.0901 0.8953 0.8115
0.250 0.3893 0.01008 0.00489 -0.0890 0.8858 0.8336
0.500 0.4137 0.00991 0.00477 -0.0877 0.8744 0.8554
0.750 0.4373 0.00969 0.00461 -0.0861 0.8632 0.8787
1.000 0.4619 0.00943 0.00441 -0.0846 0.8521 0.9100
1.250 0.4999 0.00912 0.00413 -0.0860 0.8409 1.0000
1.500 0.5308 0.00910 0.00405 -0.0866 0.8269 1.0000
1.750 0.5606 0.00910 0.00398 -0.0868 0.8120 1.0000
2.000 0.5893 0.00911 0.00393 -0.0867 0.7958 1.0000
2.250 0.6171 0.00915 0.00392 -0.0864 0.7771 1.0000
2.500 0.6447 0.00919 0.00392 -0.0860 0.7573 1.0000
2.750 0.6719 0.00926 0.00391 -0.0855 0.7354 1.0000
3.000 0.6986 0.00935 0.00391 -0.0849 0.7097 1.0000
3.250 0.7246 0.00948 0.00395 -0.0841 0.6787 1.0000
3.500 0.7498 0.00966 0.00399 -0.0832 0.6392 1.0000
3.750 0.7743 0.00994 0.00407 -0.0822 0.5942 1.0000
4.000 0.7983 0.01031 0.00421 -0.0813 0.5475 1.0000
4.250 0.8220 0.01075 0.00444 -0.0804 0.5010 1.0000
4.500 0.8455 0.01123 0.00471 -0.0795 0.4590 1.0000
4.750 0.8694 0.01171 0.00503 -0.0788 0.4209 1.0000
5.000 0.8931 0.01221 0.00537 -0.0781 0.3863 1.0000
5.250 0.9170 0.01270 0.00575 -0.0774 0.3520 1.0000
5.500 0.9407 0.01320 0.00614 -0.0768 0.3179 1.0000
5.750 0.9638 0.01376 0.00655 -0.0761 0.2813 1.0000
6.000 0.9863 0.01439 0.00701 -0.0753 0.2370 1.0000
6.250 1.0071 0.01527 0.00759 -0.0743 0.1831 1.0000
6.500 1.0266 0.01638 0.00842 -0.0732 0.1378 1.0000
6.750 1.0461 0.01749 0.00932 -0.0721 0.1139 1.0000
7.000 1.0662 0.01854 0.01028 -0.0710 0.0997 1.0000
7.250 1.0879 0.01939 0.01116 -0.0700 0.0904 1.0000
7.500 1.1082 0.02049 0.01229 -0.0689 0.0833 1.0000
7.750 1.1293 0.02141 0.01322 -0.0679 0.0770 1.0000
8.000 1.1495 0.02276 0.01457 -0.0668 0.0722 1.0000
8.250 1.1715 0.02374 0.01566 -0.0659 0.0681 1.0000
8.500 1.1926 0.02487 0.01678 -0.0651 0.0641 1.0000
8.750 1.2140 0.02663 0.01861 -0.0643 0.0605 1.0000
9.000 1.2358 0.02777 0.01994 -0.0633 0.0576 1.0000
9.250 1.2565 0.02892 0.02119 -0.0624 0.0544 1.0000
9.500 1.2769 0.03070 0.02296 -0.0618 0.0511 1.0000
9.750 1.2958 0.03267 0.02519 -0.0607 0.0486 1.0000
10.000 1.3133 0.03388 0.02664 -0.0593 0.0458 1.0000
10.250 1.3298 0.03505 0.02795 -0.0580 0.0430 1.0000
10.500 1.3463 0.03730 0.03021 -0.0572 0.0404 1.0000
10.750 1.3559 0.03972 0.03300 -0.0552 0.0384 1.0000
11.000 1.3650 0.04140 0.03498 -0.0531 0.0363 1.0000
11.250 1.3730 0.04339 0.03720 -0.0511 0.0346 1.0000
11.500 1.3787 0.04525 0.03923 -0.0490 0.0331 1.0000
11.750 1.3826 0.04728 0.04134 -0.0468 0.0320 1.0000
12.000 1.3763 0.05154 0.04582 -0.0444 0.0309 1.0000
12.250 1.3580 0.05568 0.05029 -0.0411 0.0305 1.0000
12.500 1.3434 0.05842 0.05332 -0.0387 0.0301 1.0000
12.750 1.3266 0.06202 0.05719 -0.0373 0.0298 1.0000
13.000 1.3075 0.06644 0.06189 -0.0370 0.0295 1.0000
13.250 1.2861 0.07179 0.06750 -0.0379 0.0295 1.0000
13.500 1.2629 0.07801 0.07396 -0.0401 0.0295 1.0000
13.750 1.2376 0.08532 0.08149 -0.0436 0.0296 1.0000
14.000 1.2106 0.09384 0.09021 -0.0486 0.0299 1.0000
14.250 1.1818 0.10380 0.10032 -0.0548 0.0303 1.0000
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Polar data table (+)
Polar graphs
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