S2046 (s2046-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 50,000 Max Cl/Cd: 40.1 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2046-il-50000-n5.txt Download as CSV file: xf-s2046-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4582 0.08343 0.07630 -0.0399 1.0000 0.0487
-8.250 -0.4635 0.07909 0.07204 -0.0418 1.0000 0.0486
-8.000 -0.4683 0.07378 0.06680 -0.0457 1.0000 0.0485
-7.750 -0.4735 0.06874 0.06177 -0.0492 1.0000 0.0483
-7.500 -0.4785 0.06372 0.05668 -0.0523 1.0000 0.0484
-7.250 -0.4813 0.05863 0.05142 -0.0552 1.0000 0.0485
-7.000 -0.4787 0.05415 0.04676 -0.0570 1.0000 0.0492
-6.750 -0.4686 0.05178 0.04439 -0.0568 1.0000 0.0507
-6.500 -0.4585 0.04828 0.04067 -0.0577 1.0000 0.0519
-6.250 -0.4458 0.04424 0.03623 -0.0590 1.0000 0.0526
-6.000 -0.4294 0.04047 0.03202 -0.0601 1.0000 0.0535
-5.750 -0.4102 0.03706 0.02814 -0.0608 1.0000 0.0550
-5.500 -0.3887 0.03398 0.02455 -0.0611 1.0000 0.0571
-5.250 -0.3652 0.03129 0.02123 -0.0612 1.0000 0.0608
-5.000 -0.3447 0.02995 0.01991 -0.0608 1.0000 0.0660
-4.750 -0.3211 0.02815 0.01766 -0.0603 1.0000 0.0727
-4.500 -0.2993 0.02684 0.01633 -0.0598 1.0000 0.0808
-4.250 -0.2766 0.02565 0.01501 -0.0592 1.0000 0.0931
-4.000 -0.2539 0.02464 0.01391 -0.0587 1.0000 0.1092
-3.750 -0.2310 0.02371 0.01287 -0.0581 1.0000 0.1277
-3.500 -0.2086 0.02285 0.01197 -0.0574 1.0000 0.1468
-3.250 -0.1854 0.02204 0.01117 -0.0570 1.0000 0.1664
-3.000 -0.1607 0.02133 0.01050 -0.0569 1.0000 0.1945
-2.750 -0.1352 0.02061 0.00989 -0.0572 1.0000 0.2333
-2.500 -0.1091 0.01976 0.00947 -0.0577 1.0000 0.3081
-2.250 -0.0866 0.01917 0.00959 -0.0570 1.0000 0.4505
-2.000 -0.0674 0.01911 0.00978 -0.0552 1.0000 0.5556
-1.750 -0.0493 0.01918 0.00992 -0.0532 1.0000 0.6234
-1.500 -0.0249 0.01931 0.01009 -0.0523 0.9955 0.6823
-1.250 0.0046 0.01944 0.01022 -0.0522 0.9865 0.7392
-1.000 0.0315 0.01945 0.01028 -0.0515 0.9771 0.7954
-0.750 0.0575 0.01928 0.01022 -0.0503 0.9677 0.8608
-0.500 0.1017 0.01900 0.00994 -0.0535 0.9570 1.0000
-0.250 0.1429 0.01922 0.00993 -0.0570 0.9466 1.0000
0.000 0.1851 0.01946 0.00996 -0.0606 0.9362 1.0000
0.250 0.2297 0.01968 0.01001 -0.0643 0.9263 1.0000
0.500 0.2700 0.01986 0.01006 -0.0670 0.9143 1.0000
0.750 0.3095 0.02002 0.01012 -0.0694 0.9019 1.0000
1.000 0.3490 0.02015 0.01018 -0.0717 0.8893 1.0000
1.250 0.3877 0.02025 0.01024 -0.0737 0.8762 1.0000
1.500 0.4245 0.02032 0.01028 -0.0752 0.8624 1.0000
1.750 0.4603 0.02035 0.01031 -0.0763 0.8479 1.0000
2.000 0.4952 0.02036 0.01035 -0.0772 0.8329 1.0000
2.250 0.5292 0.02035 0.01037 -0.0778 0.8171 1.0000
2.500 0.5626 0.02032 0.01037 -0.0782 0.8005 1.0000
2.750 0.5958 0.02026 0.01037 -0.0784 0.7831 1.0000
3.000 0.6251 0.02027 0.01045 -0.0780 0.7626 1.0000
3.250 0.6554 0.02024 0.01046 -0.0776 0.7414 1.0000
3.500 0.6844 0.02024 0.01052 -0.0770 0.7178 1.0000
3.750 0.7141 0.02021 0.01056 -0.0763 0.6931 1.0000
4.000 0.7420 0.02026 0.01064 -0.0754 0.6650 1.0000
4.250 0.7690 0.02037 0.01076 -0.0745 0.6341 1.0000
4.500 0.7951 0.02056 0.01099 -0.0734 0.6001 1.0000
4.750 0.8209 0.02080 0.01116 -0.0722 0.5643 1.0000
5.000 0.8451 0.02117 0.01144 -0.0709 0.5254 1.0000
5.250 0.8681 0.02165 0.01177 -0.0695 0.4849 1.0000
5.500 0.8898 0.02226 0.01220 -0.0681 0.4438 1.0000
5.750 0.9104 0.02298 0.01282 -0.0667 0.4028 1.0000
6.000 0.9303 0.02377 0.01350 -0.0653 0.3626 1.0000
6.250 0.9496 0.02464 0.01425 -0.0640 0.3238 1.0000
6.500 0.9679 0.02560 0.01510 -0.0627 0.2839 1.0000
6.750 0.9859 0.02667 0.01611 -0.0614 0.2439 1.0000
7.000 1.0032 0.02790 0.01719 -0.0602 0.2074 1.0000
7.250 1.0209 0.02928 0.01844 -0.0590 0.1779 1.0000
7.500 1.0381 0.03074 0.01976 -0.0578 0.1550 1.0000
7.750 1.0570 0.03225 0.02125 -0.0568 0.1383 1.0000
8.000 1.0760 0.03380 0.02283 -0.0558 0.1255 1.0000
8.250 1.0946 0.03535 0.02440 -0.0548 0.1143 1.0000
8.500 1.1158 0.03704 0.02628 -0.0539 0.1056 1.0000
8.750 1.1366 0.03887 0.02808 -0.0531 0.0994 1.0000
9.000 1.1565 0.04075 0.03029 -0.0522 0.0923 1.0000
9.250 1.1754 0.04267 0.03212 -0.0515 0.0867 1.0000
9.500 1.1945 0.04514 0.03512 -0.0505 0.0824 1.0000
9.750 1.2107 0.04753 0.03778 -0.0494 0.0782 1.0000
10.000 1.2279 0.04980 0.03999 -0.0488 0.0741 1.0000
10.250 1.2337 0.05281 0.04359 -0.0469 0.0709 1.0000
10.500 1.2391 0.05615 0.04737 -0.0453 0.0686 1.0000
10.750 1.2412 0.05946 0.05103 -0.0436 0.0665 1.0000
11.000 1.2422 0.06240 0.05419 -0.0420 0.0643 1.0000
11.250 1.2488 0.06511 0.05688 -0.0410 0.0619 1.0000
11.500 1.2318 0.06892 0.06104 -0.0387 0.0611 1.0000
11.750 1.2110 0.07329 0.06576 -0.0375 0.0605 1.0000
12.000 1.1883 0.07838 0.07115 -0.0376 0.0603 1.0000
12.250 1.1636 0.08434 0.07736 -0.0393 0.0603 1.0000
12.500 1.1371 0.09139 0.08462 -0.0425 0.0605 1.0000
12.750 1.1100 0.09961 0.09300 -0.0472 0.0609 1.0000
13.000 1.0831 0.10907 0.10257 -0.0532 0.0614 1.0000
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Polar data table (+)
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