NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il) Reynolds number: 200,000 Max Cl/Cd: 36.46 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20518-il-200000.txt Download as CSV file: xf-sc20518-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0518 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9356 0.09457 0.08901 -0.0623 1.0000 0.0717
-17.000 -0.9973 0.08290 0.07699 -0.0683 1.0000 0.0716
-16.750 -1.0438 0.07478 0.06854 -0.0717 1.0000 0.0717
-16.500 -1.0241 0.07349 0.06736 -0.0713 1.0000 0.0727
-16.250 -1.0177 0.07138 0.06525 -0.0717 1.0000 0.0735
-16.000 -1.0171 0.06876 0.06259 -0.0722 1.0000 0.0743
-15.750 -1.0296 0.06495 0.05863 -0.0730 1.0000 0.0749
-15.500 -1.0432 0.06120 0.05470 -0.0735 1.0000 0.0756
-15.250 -1.0564 0.05767 0.05097 -0.0736 1.0000 0.0763
-15.000 -1.0687 0.05439 0.04748 -0.0734 1.0000 0.0770
-14.750 -1.0804 0.05139 0.04425 -0.0728 1.0000 0.0778
-14.500 -1.0925 0.04869 0.04129 -0.0718 1.0000 0.0785
-14.250 -1.1056 0.04639 0.03873 -0.0701 1.0000 0.0791
-14.000 -1.0791 0.04508 0.03753 -0.0700 1.0000 0.0805
-13.750 -1.0675 0.04401 0.03648 -0.0691 1.0000 0.0816
-13.500 -1.0604 0.04284 0.03527 -0.0678 1.0000 0.0828
-13.250 -1.0560 0.04162 0.03397 -0.0661 1.0000 0.0841
-13.000 -1.0562 0.04033 0.03257 -0.0638 1.0000 0.0853
-12.750 -1.0612 0.03915 0.03123 -0.0607 1.0000 0.0863
-12.500 -1.0721 0.03821 0.03014 -0.0564 1.0000 0.0870
-12.250 -1.0410 0.03700 0.02903 -0.0568 1.0000 0.0888
-12.000 -1.0323 0.03633 0.02840 -0.0545 1.0000 0.0900
-11.750 -1.0323 0.03570 0.02775 -0.0510 1.0000 0.0912
-11.500 -1.0318 0.03500 0.02701 -0.0478 1.0000 0.0925
-11.250 -1.0292 0.03425 0.02619 -0.0449 1.0000 0.0939
-11.000 -1.0269 0.03348 0.02530 -0.0422 1.0000 0.0952
-10.750 -1.0175 0.03264 0.02439 -0.0400 1.0000 0.0966
-10.500 -1.0013 0.03201 0.02386 -0.0381 1.0000 0.0983
-10.250 -0.9908 0.03144 0.02333 -0.0360 1.0000 0.0999
-10.000 -0.9809 0.03085 0.02272 -0.0341 1.0000 0.1016
-9.750 -0.9705 0.03022 0.02203 -0.0323 1.0000 0.1035
-9.500 -0.9589 0.02962 0.02131 -0.0309 1.0000 0.1053
-9.250 -0.9441 0.02898 0.02074 -0.0288 1.0000 0.1072
-9.000 -0.9149 0.02839 0.02025 -0.0298 0.9978 0.1099
-8.750 -0.8801 0.02778 0.01963 -0.0320 0.9945 0.1133
-8.500 -0.8435 0.02718 0.01893 -0.0345 0.9917 0.1165
-8.250 -0.8137 0.02653 0.01844 -0.0351 0.9880 0.1200
-8.000 -0.7805 0.02595 0.01788 -0.0369 0.9837 0.1242
-7.750 -0.7458 0.02537 0.01728 -0.0390 0.9804 0.1287
-7.500 -0.7101 0.02470 0.01676 -0.0413 0.9778 0.1340
-7.250 -0.6810 0.02413 0.01615 -0.0425 0.9720 0.1397
-7.000 -0.6486 0.02331 0.01550 -0.0445 0.9675 0.1468
-6.750 -0.6106 0.02257 0.01482 -0.0476 0.9644 0.1560
-6.500 -0.5735 0.02185 0.01415 -0.0507 0.9612 0.1679
-6.250 -0.5451 0.02094 0.01340 -0.0526 0.9545 0.1827
-6.000 -0.5050 0.01974 0.01248 -0.0572 0.9512 0.2109
-5.750 -0.4571 0.01805 0.01130 -0.0643 0.9492 0.2826
-5.500 -0.4019 0.01623 0.01047 -0.0730 0.9483 0.4392
-5.250 -0.3590 0.01647 0.01105 -0.0756 0.9464 0.5162
-5.000 -0.3331 0.01680 0.01141 -0.0751 0.9379 0.5420
-4.750 -0.2939 0.01716 0.01175 -0.0768 0.9342 0.5616
-4.500 -0.2527 0.01755 0.01210 -0.0788 0.9317 0.5767
-4.250 -0.2081 0.01788 0.01236 -0.0817 0.9301 0.5909
-4.000 -0.1919 0.01857 0.01312 -0.0784 0.9210 0.5963
-3.750 -0.1595 0.01918 0.01376 -0.0779 0.9171 0.6028
-3.500 -0.1170 0.01928 0.01379 -0.0807 0.9147 0.6135
-3.250 -0.0868 0.02008 0.01465 -0.0790 0.9123 0.6171
-3.000 -0.0719 0.02086 0.01548 -0.0754 0.9029 0.6213
-2.750 -0.0288 0.02062 0.01515 -0.0791 0.8994 0.6329
-2.500 -0.0012 0.02121 0.01579 -0.0771 0.8959 0.6352
-2.250 0.0256 0.02216 0.01681 -0.0742 0.8933 0.6382
-2.000 0.0356 0.02325 0.01796 -0.0691 0.8835 0.6421
-1.750 0.0758 0.02304 0.01770 -0.0722 0.8795 0.6551
-1.500 0.1025 0.02355 0.01825 -0.0697 0.8759 0.6571
-1.250 0.1325 0.02386 0.01858 -0.0683 0.8730 0.6592
-1.000 0.1461 0.02427 0.01903 -0.0649 0.8621 0.6625
-0.750 0.2012 0.02308 0.01773 -0.0719 0.8561 0.6753
-0.500 0.2227 0.02289 0.01755 -0.0690 0.8444 0.6772
-0.250 0.2520 0.02255 0.01718 -0.0672 0.8349 0.6787
0.000 0.2738 0.02246 0.01711 -0.0651 0.8233 0.6807
0.250 0.3028 0.02223 0.01685 -0.0640 0.8143 0.6834
0.500 0.3275 0.02210 0.01674 -0.0631 0.8033 0.6872
0.750 0.3627 0.02157 0.01616 -0.0649 0.7944 0.6913
1.000 0.4080 0.02064 0.01517 -0.0707 0.7818 0.6982
1.250 0.4338 0.02037 0.01486 -0.0692 0.7707 0.6996
1.500 0.4549 0.02025 0.01477 -0.0671 0.7559 0.7012
1.750 0.4789 0.02011 0.01465 -0.0656 0.7417 0.7031
2.000 0.5061 0.01989 0.01440 -0.0651 0.7269 0.7050
2.250 0.5344 0.01962 0.01410 -0.0650 0.7096 0.7071
2.500 0.5633 0.01936 0.01380 -0.0652 0.6887 0.7093
2.750 0.5930 0.01909 0.01349 -0.0658 0.6623 0.7118
3.000 0.6246 0.01883 0.01311 -0.0669 0.6282 0.7146
3.250 0.6597 0.01865 0.01269 -0.0693 0.5705 0.7186
3.500 0.6807 0.01896 0.01247 -0.0684 0.4728 0.7212
3.750 0.6886 0.01979 0.01275 -0.0647 0.3796 0.7228
4.000 0.6987 0.02061 0.01318 -0.0615 0.3109 0.7244
4.250 0.7127 0.02133 0.01360 -0.0592 0.2606 0.7262
4.500 0.7309 0.02193 0.01397 -0.0578 0.2263 0.7279
4.750 0.7509 0.02250 0.01434 -0.0569 0.2034 0.7298
5.000 0.7724 0.02304 0.01474 -0.0562 0.1870 0.7322
5.250 0.7967 0.02353 0.01514 -0.0562 0.1740 0.7350
5.500 0.8248 0.02394 0.01550 -0.0569 0.1634 0.7374
5.750 0.8538 0.02449 0.01593 -0.0581 0.1547 0.7399
6.000 0.8859 0.02490 0.01628 -0.0599 0.1469 0.7424
6.250 0.9058 0.02545 0.01678 -0.0586 0.1415 0.7438
6.500 0.9269 0.02583 0.01720 -0.0575 0.1362 0.7453
6.750 0.9477 0.02644 0.01772 -0.0565 0.1316 0.7470
7.000 0.9697 0.02697 0.01830 -0.0556 0.1275 0.7487
7.250 0.9915 0.02744 0.01879 -0.0547 0.1234 0.7508
7.500 1.0164 0.02818 0.01941 -0.0546 0.1196 0.7531
7.750 1.0415 0.02881 0.02011 -0.0545 0.1162 0.7561
8.000 1.0676 0.02939 0.02071 -0.0547 0.1126 0.7593
8.250 1.0996 0.03016 0.02135 -0.0563 0.1093 0.7623
8.500 1.1262 0.03095 0.02219 -0.0565 0.1062 0.7644
8.750 1.1442 0.03153 0.02288 -0.0549 0.1036 0.7662
9.000 1.1646 0.03218 0.02354 -0.0538 0.1012 0.7682
9.250 1.1995 0.03340 0.02459 -0.0554 0.0983 0.7703
9.500 1.2129 0.03398 0.02538 -0.0532 0.0963 0.7729
9.750 1.2305 0.03472 0.02624 -0.0519 0.0940 0.7758
10.000 1.2532 0.03550 0.02703 -0.0517 0.0918 0.7791
10.250 1.2913 0.03670 0.02807 -0.0542 0.0896 0.7825
10.500 1.3059 0.03770 0.02926 -0.0524 0.0880 0.7851
10.750 1.3176 0.03864 0.03039 -0.0501 0.0863 0.7876
11.000 1.3316 0.03959 0.03146 -0.0483 0.0846 0.7905
11.250 1.3489 0.04050 0.03239 -0.0472 0.0830 0.7938
11.500 1.3777 0.04162 0.03339 -0.0479 0.0814 0.7972
11.750 1.3920 0.04321 0.03519 -0.0469 0.0800 0.8009
12.000 1.4005 0.04472 0.03694 -0.0450 0.0788 0.8039
12.250 1.4082 0.04613 0.03854 -0.0427 0.0776 0.8064
12.500 1.4183 0.04751 0.04003 -0.0410 0.0765 0.8094
12.750 1.4292 0.04887 0.04148 -0.0395 0.0754 0.8129
13.000 1.4461 0.05017 0.04278 -0.0390 0.0744 0.8170
13.250 1.4683 0.05218 0.04478 -0.0394 0.0732 0.8212
13.500 1.4555 0.05442 0.04736 -0.0357 0.0726 0.8239
13.750 1.4435 0.05704 0.05030 -0.0328 0.0719 0.8270
14.000 1.4328 0.05996 0.05350 -0.0306 0.0712 0.8304
14.250 1.4228 0.06313 0.05693 -0.0292 0.0705 0.8340
14.500 1.4134 0.06664 0.06066 -0.0284 0.0699 0.8375
14.750 1.4013 0.07022 0.06446 -0.0275 0.0693 0.8402
15.000 1.3876 0.07400 0.06845 -0.0269 0.0689 0.8428
15.250 1.3721 0.07826 0.07293 -0.0268 0.0685 0.8456
15.500 1.3590 0.08258 0.07741 -0.0273 0.0681 0.8487
15.750 1.3342 0.08862 0.08370 -0.0290 0.0679 0.8514
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Polar data table (+)
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