S2046 (s2046-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 500,000 Max Cl/Cd: 101.89 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2046-il-500000.txt Download as CSV file: xf-s2046-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3554 0.08643 0.08420 -0.0347 1.0000 0.0293
-9.500 -0.3577 0.08158 0.07938 -0.0364 1.0000 0.0294
-9.250 -0.3761 0.07343 0.07126 -0.0385 1.0000 0.0301
-9.000 -0.3735 0.07050 0.06835 -0.0383 1.0000 0.0306
-8.750 -0.3727 0.06739 0.06525 -0.0384 1.0000 0.0310
-8.500 -0.3753 0.06374 0.06164 -0.0389 1.0000 0.0313
-8.250 -0.3805 0.06002 0.05795 -0.0394 1.0000 0.0317
-8.000 -0.3925 0.05591 0.05389 -0.0398 1.0000 0.0319
-7.750 -0.4153 0.05269 0.05074 -0.0381 1.0000 0.0320
-7.500 -0.5431 0.02389 0.01961 -0.0701 0.9955 0.0180
-7.250 -0.5100 0.02071 0.01592 -0.0728 0.9936 0.0178
-7.000 -0.4782 0.01858 0.01351 -0.0746 0.9909 0.0180
-6.750 -0.4449 0.01701 0.01174 -0.0764 0.9883 0.0183
-6.500 -0.4105 0.01581 0.01039 -0.0782 0.9861 0.0189
-6.250 -0.3750 0.01478 0.00924 -0.0801 0.9843 0.0193
-6.000 -0.3393 0.01386 0.00820 -0.0820 0.9826 0.0199
-5.750 -0.3081 0.01312 0.00738 -0.0829 0.9784 0.0206
-5.500 -0.2734 0.01253 0.00671 -0.0844 0.9755 0.0217
-5.250 -0.2373 0.01191 0.00602 -0.0862 0.9733 0.0225
-5.000 -0.2003 0.01093 0.00496 -0.0883 0.9715 0.0243
-4.750 -0.1626 0.01044 0.00445 -0.0905 0.9701 0.0273
-4.500 -0.1320 0.00996 0.00395 -0.0910 0.9647 0.0327
-4.250 -0.0981 0.00945 0.00355 -0.0923 0.9608 0.0570
-4.000 -0.0633 0.00921 0.00334 -0.0937 0.9576 0.0730
-3.750 -0.0322 0.00897 0.00313 -0.0943 0.9524 0.0862
-3.500 -0.0019 0.00872 0.00292 -0.0947 0.9460 0.1008
-3.250 0.0294 0.00843 0.00268 -0.0953 0.9408 0.1197
-3.000 0.0567 0.00816 0.00248 -0.0950 0.9315 0.1452
-2.750 0.0846 0.00778 0.00228 -0.0950 0.9228 0.1959
-2.500 0.1119 0.00728 0.00207 -0.0949 0.9138 0.2922
-2.250 0.1385 0.00684 0.00198 -0.0947 0.9039 0.4044
-2.000 0.1658 0.00664 0.00193 -0.0944 0.8949 0.4725
-1.750 0.1930 0.00652 0.00189 -0.0940 0.8855 0.5178
-1.500 0.2201 0.00645 0.00187 -0.0936 0.8754 0.5536
-1.250 0.2475 0.00640 0.00185 -0.0933 0.8661 0.5822
-1.000 0.2750 0.00636 0.00182 -0.0929 0.8564 0.6054
-0.750 0.3023 0.00633 0.00180 -0.0925 0.8458 0.6252
-0.500 0.3298 0.00631 0.00179 -0.0921 0.8356 0.6431
-0.250 0.3573 0.00632 0.00177 -0.0918 0.8250 0.6604
0.000 0.3847 0.00632 0.00177 -0.0914 0.8133 0.6768
0.250 0.4118 0.00631 0.00179 -0.0910 0.8010 0.6970
0.500 0.4388 0.00632 0.00183 -0.0905 0.7881 0.7200
0.750 0.4657 0.00633 0.00186 -0.0900 0.7747 0.7403
1.000 0.4926 0.00635 0.00188 -0.0895 0.7603 0.7574
1.250 0.5195 0.00637 0.00190 -0.0891 0.7447 0.7730
1.500 0.5462 0.00640 0.00193 -0.0886 0.7278 0.7887
1.750 0.5725 0.00645 0.00196 -0.0880 0.7090 0.8053
2.000 0.5986 0.00648 0.00200 -0.0874 0.6871 0.8240
2.250 0.6237 0.00653 0.00204 -0.0866 0.6616 0.8454
2.500 0.6472 0.00658 0.00208 -0.0854 0.6293 0.8759
2.750 0.6725 0.00660 0.00207 -0.0845 0.5839 1.0000
3.000 0.6982 0.00696 0.00217 -0.0841 0.5344 1.0000
3.250 0.7237 0.00734 0.00233 -0.0837 0.4868 1.0000
3.500 0.7493 0.00772 0.00251 -0.0834 0.4449 1.0000
3.750 0.7754 0.00805 0.00269 -0.0831 0.4110 1.0000
4.000 0.8013 0.00840 0.00290 -0.0828 0.3775 1.0000
4.250 0.8272 0.00875 0.00312 -0.0824 0.3466 1.0000
4.500 0.8531 0.00910 0.00334 -0.0821 0.3173 1.0000
4.750 0.8788 0.00946 0.00358 -0.0818 0.2888 1.0000
5.000 0.9046 0.00982 0.00382 -0.0815 0.2619 1.0000
5.250 0.9299 0.01022 0.00411 -0.0811 0.2324 1.0000
5.500 0.9545 0.01071 0.00442 -0.0807 0.1968 1.0000
5.750 0.9784 0.01130 0.00480 -0.0801 0.1560 1.0000
6.000 1.0019 0.01195 0.00524 -0.0795 0.1188 1.0000
6.250 1.0255 0.01257 0.00573 -0.0789 0.0939 1.0000
6.500 1.0494 0.01315 0.00623 -0.0784 0.0789 1.0000
6.750 1.0736 0.01367 0.00673 -0.0778 0.0693 1.0000
7.000 1.0965 0.01435 0.00736 -0.0770 0.0614 1.0000
7.250 1.1213 0.01475 0.00783 -0.0765 0.0574 1.0000
7.500 1.1444 0.01537 0.00843 -0.0758 0.0526 1.0000
7.750 1.1667 0.01605 0.00917 -0.0749 0.0490 1.0000
8.000 1.1905 0.01653 0.00971 -0.0743 0.0464 1.0000
8.250 1.2134 0.01708 0.01029 -0.0736 0.0438 1.0000
8.500 1.2329 0.01805 0.01129 -0.0724 0.0405 1.0000
8.750 1.2548 0.01868 0.01200 -0.0715 0.0386 1.0000
9.000 1.2782 0.01909 0.01246 -0.0709 0.0364 1.0000
9.250 1.3007 0.01957 0.01298 -0.0702 0.0342 1.0000
9.500 1.3196 0.02044 0.01387 -0.0690 0.0320 1.0000
9.750 1.3357 0.02164 0.01517 -0.0674 0.0302 1.0000
10.000 1.3574 0.02213 0.01576 -0.0665 0.0289 1.0000
10.250 1.3780 0.02266 0.01636 -0.0656 0.0271 1.0000
10.500 1.3980 0.02321 0.01694 -0.0646 0.0254 1.0000
10.750 1.4064 0.02496 0.01875 -0.0622 0.0232 1.0000
11.000 1.4266 0.02537 0.01926 -0.0612 0.0222 1.0000
11.250 1.4430 0.02603 0.02001 -0.0597 0.0208 1.0000
11.500 1.4570 0.02669 0.02075 -0.0579 0.0195 1.0000
11.750 1.4657 0.02772 0.02181 -0.0554 0.0184 1.0000
12.000 1.4638 0.02971 0.02392 -0.0520 0.0172 1.0000
12.250 1.4742 0.03070 0.02505 -0.0501 0.0165 1.0000
12.500 1.4819 0.03195 0.02641 -0.0481 0.0157 1.0000
12.750 1.4895 0.03321 0.02777 -0.0464 0.0149 1.0000
13.000 1.4956 0.03464 0.02927 -0.0447 0.0142 1.0000
13.250 1.4978 0.03652 0.03122 -0.0431 0.0136 1.0000
13.500 1.4891 0.03967 0.03451 -0.0413 0.0131 1.0000
13.750 1.4863 0.04244 0.03745 -0.0402 0.0127 1.0000
14.000 1.4874 0.04489 0.04005 -0.0395 0.0124 1.0000
14.250 1.4849 0.04792 0.04325 -0.0392 0.0121 1.0000
14.500 1.4810 0.05130 0.04680 -0.0392 0.0118 1.0000
14.750 1.4753 0.05513 0.05079 -0.0398 0.0116 1.0000
15.000 1.4685 0.05935 0.05517 -0.0408 0.0114 1.0000
15.250 1.4602 0.06404 0.06001 -0.0424 0.0111 1.0000
15.500 1.4496 0.06940 0.06553 -0.0446 0.0110 1.0000
15.750 1.4382 0.07525 0.07154 -0.0473 0.0109 1.0000
16.000 1.4252 0.08171 0.07816 -0.0506 0.0108 1.0000
16.250 1.4104 0.08886 0.08547 -0.0545 0.0107 1.0000
16.500 1.3945 0.09652 0.09329 -0.0588 0.0107 1.0000
16.750 1.3763 0.10492 0.10186 -0.0636 0.0106 1.0000
17.000 1.3572 0.11380 0.11091 -0.0689 0.0106 1.0000
17.250 1.3352 0.12361 0.12090 -0.0749 0.0106 1.0000
17.500 1.3106 0.13451 0.13198 -0.0817 0.0107 1.0000
17.750 1.2806 0.14727 0.14495 -0.0898 0.0109 1.0000
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Polar data table (+)
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