SG6040 (sg6040-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6040 (sg6040-il) Reynolds number: 200,000 Max Cl/Cd: 72.93 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6040-il-200000.txt Download as CSV file: xf-sg6040-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SG6040
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3025 0.12759 0.12410 -0.0514 1.0000 0.0724
-13.000 -0.6267 0.07101 0.06665 -0.0820 1.0000 0.0341
-12.750 -0.6455 0.06627 0.06184 -0.0831 1.0000 0.0339
-12.500 -0.6686 0.06187 0.05734 -0.0838 1.0000 0.0337
-12.250 -0.6877 0.05828 0.05367 -0.0833 1.0000 0.0335
-12.000 -0.7126 0.05494 0.05022 -0.0820 1.0000 0.0333
-11.750 -0.7382 0.05229 0.04746 -0.0794 1.0000 0.0332
-11.500 -0.7649 0.05050 0.04558 -0.0754 1.0000 0.0332
-11.250 -0.7936 0.04921 0.04424 -0.0700 1.0000 0.0330
-11.000 -0.8270 0.04860 0.04358 -0.0632 1.0000 0.0331
-10.750 -0.8489 0.04697 0.04183 -0.0583 1.0000 0.0328
-10.500 -0.8439 0.04361 0.03808 -0.0593 0.9954 0.0330
-10.250 -0.8278 0.04018 0.03417 -0.0614 0.9891 0.0335
-10.000 -0.8044 0.03721 0.03075 -0.0636 0.9840 0.0338
-9.750 -0.7821 0.03487 0.02806 -0.0645 0.9783 0.0340
-9.500 -0.7541 0.03272 0.02560 -0.0660 0.9737 0.0343
-9.250 -0.7211 0.03048 0.02328 -0.0681 0.9713 0.0350
-9.000 -0.6960 0.02909 0.02185 -0.0685 0.9653 0.0357
-8.750 -0.6644 0.02777 0.02046 -0.0699 0.9610 0.0366
-8.500 -0.6286 0.02649 0.01908 -0.0721 0.9582 0.0381
-8.250 -0.6046 0.02553 0.01799 -0.0720 0.9514 0.0397
-8.000 -0.5745 0.02427 0.01681 -0.0734 0.9469 0.0420
-7.750 -0.5385 0.02326 0.01576 -0.0756 0.9440 0.0452
-7.500 -0.5184 0.02226 0.01477 -0.0749 0.9363 0.0482
-7.250 -0.4862 0.02135 0.01382 -0.0764 0.9318 0.0541
-7.000 -0.4513 0.02010 0.01273 -0.0787 0.9289 0.0686
-6.750 -0.4308 0.01935 0.01208 -0.0780 0.9210 0.0930
-6.500 -0.3967 0.01865 0.01145 -0.0799 0.9167 0.1158
-6.250 -0.3570 0.01800 0.01081 -0.0827 0.9143 0.1349
-6.000 -0.3160 0.01735 0.01016 -0.0857 0.9125 0.1547
-5.750 -0.2972 0.01690 0.00981 -0.0844 0.9033 0.1740
-5.500 -0.2630 0.01612 0.00919 -0.0863 0.8994 0.2075
-5.250 -0.2281 0.01506 0.00845 -0.0884 0.8965 0.2660
-4.750 -0.1830 0.01349 0.00790 -0.0874 0.8826 0.4772
-4.500 -0.1456 0.01342 0.00785 -0.0888 0.8794 0.5377
-4.250 -0.1232 0.01359 0.00803 -0.0874 0.8705 0.5641
-4.000 -0.0892 0.01363 0.00796 -0.0882 0.8655 0.5869
-3.750 -0.0522 0.01367 0.00790 -0.0895 0.8619 0.6052
-3.500 -0.0310 0.01387 0.00811 -0.0878 0.8523 0.6171
-3.250 0.0025 0.01389 0.00805 -0.0884 0.8472 0.6294
-3.000 0.0294 0.01399 0.00806 -0.0880 0.8397 0.6417
-2.750 0.0578 0.01409 0.00815 -0.0875 0.8327 0.6508
-2.500 0.0919 0.01409 0.00806 -0.0883 0.8279 0.6620
-2.250 0.1134 0.01428 0.00826 -0.0867 0.8184 0.6723
-2.000 0.1441 0.01436 0.00830 -0.0866 0.8126 0.6827
-1.750 0.1686 0.01448 0.00836 -0.0858 0.8041 0.6942
-1.500 0.1963 0.01456 0.00846 -0.0850 0.7972 0.7016
-1.250 0.2243 0.01458 0.00838 -0.0850 0.7900 0.7114
-1.000 0.2495 0.01460 0.00842 -0.0840 0.7820 0.7167
-0.750 0.2805 0.01457 0.00830 -0.0844 0.7762 0.7235
-0.500 0.3041 0.01453 0.00824 -0.0837 0.7668 0.7299
-0.250 0.3344 0.01447 0.00812 -0.0838 0.7607 0.7342
0.000 0.3581 0.01447 0.00812 -0.0831 0.7517 0.7394
0.250 0.3891 0.01437 0.00792 -0.0838 0.7448 0.7450
0.500 0.4137 0.01434 0.00790 -0.0831 0.7363 0.7489
0.750 0.4419 0.01428 0.00781 -0.0830 0.7289 0.7531
1.000 0.4684 0.01427 0.00777 -0.0828 0.7208 0.7579
1.250 0.4975 0.01422 0.00765 -0.0833 0.7128 0.7631
1.500 0.5233 0.01419 0.00763 -0.0827 0.7048 0.7667
1.750 0.5502 0.01416 0.00759 -0.0825 0.6965 0.7708
2.000 0.5777 0.01417 0.00758 -0.0825 0.6886 0.7758
2.250 0.6053 0.01416 0.00753 -0.0826 0.6800 0.7808
2.500 0.6317 0.01417 0.00754 -0.0822 0.6722 0.7845
2.750 0.6575 0.01418 0.00758 -0.0818 0.6635 0.7892
3.000 0.6853 0.01423 0.00759 -0.0819 0.6555 0.7947
3.250 0.7113 0.01424 0.00762 -0.0816 0.6467 0.7993
3.500 0.7375 0.01430 0.00769 -0.0813 0.6388 0.8038
3.750 0.7632 0.01435 0.00776 -0.0809 0.6298 0.8097
4.000 0.7900 0.01442 0.00783 -0.0808 0.6216 0.8154
4.250 0.8147 0.01446 0.00792 -0.0802 0.6127 0.8205
4.500 0.8398 0.01454 0.00802 -0.0797 0.6035 0.8269
4.750 0.8660 0.01457 0.00803 -0.0794 0.5940 0.8333
5.000 0.8875 0.01463 0.00817 -0.0781 0.5831 0.8402
5.250 0.9135 0.01469 0.00820 -0.0778 0.5729 0.8480
5.500 0.9345 0.01470 0.00827 -0.0763 0.5619 0.8552
5.750 0.9567 0.01478 0.00840 -0.0753 0.5507 0.8645
6.000 0.9780 0.01481 0.00845 -0.0739 0.5399 0.8739
6.250 0.9969 0.01484 0.00853 -0.0721 0.5281 0.8852
6.500 1.0150 0.01490 0.00867 -0.0702 0.5166 0.8986
6.750 1.0339 0.01494 0.00875 -0.0684 0.5057 0.9142
7.000 1.0522 0.01497 0.00882 -0.0664 0.4940 0.9352
7.250 1.0800 0.01505 0.00899 -0.0667 0.4791 0.9676
7.500 1.1089 0.01525 0.00919 -0.0677 0.4631 1.0000
7.750 1.1312 0.01551 0.00944 -0.0673 0.4474 1.0000
8.000 1.1508 0.01580 0.00971 -0.0662 0.4311 1.0000
8.250 1.1677 0.01613 0.01000 -0.0647 0.4143 1.0000
8.500 1.1811 0.01648 0.01032 -0.0624 0.3972 1.0000
8.750 1.1926 0.01691 0.01071 -0.0598 0.3792 1.0000
9.000 1.2026 0.01741 0.01118 -0.0570 0.3592 1.0000
9.250 1.2110 0.01801 0.01173 -0.0541 0.3365 1.0000
9.500 1.2164 0.01877 0.01239 -0.0509 0.3127 1.0000
9.750 1.2200 0.01969 0.01320 -0.0477 0.2850 1.0000
10.000 1.2216 0.02080 0.01419 -0.0444 0.2561 1.0000
10.250 1.2209 0.02215 0.01539 -0.0412 0.2275 1.0000
10.500 1.2187 0.02373 0.01681 -0.0381 0.2020 1.0000
10.750 1.2177 0.02539 0.01835 -0.0353 0.1792 1.0000
11.000 1.2162 0.02720 0.02003 -0.0328 0.1610 1.0000
11.250 1.2151 0.02909 0.02184 -0.0306 0.1455 1.0000
11.500 1.2158 0.03097 0.02366 -0.0287 0.1322 1.0000
11.750 1.2178 0.03285 0.02553 -0.0271 0.1208 1.0000
12.000 1.2196 0.03482 0.02749 -0.0256 0.1115 1.0000
12.250 1.2184 0.03709 0.02968 -0.0241 0.1042 1.0000
12.500 1.2241 0.03890 0.03156 -0.0231 0.0970 1.0000
12.750 1.2233 0.04129 0.03386 -0.0218 0.0914 1.0000
13.000 1.2305 0.04309 0.03578 -0.0211 0.0862 1.0000
13.250 1.2341 0.04522 0.03791 -0.0203 0.0819 1.0000
13.500 1.2390 0.04731 0.04001 -0.0195 0.0780 1.0000
13.750 1.2454 0.04930 0.04209 -0.0190 0.0742 1.0000
14.000 1.2510 0.05140 0.04418 -0.0185 0.0711 1.0000
14.250 1.2590 0.05330 0.04607 -0.0178 0.0681 1.0000
14.500 1.2661 0.05535 0.04825 -0.0175 0.0655 1.0000
14.750 1.2733 0.05741 0.05037 -0.0172 0.0631 1.0000
15.000 1.2814 0.05937 0.05231 -0.0169 0.0608 1.0000
15.250 1.2928 0.06112 0.05409 -0.0163 0.0585 1.0000
15.500 1.2987 0.06344 0.05657 -0.0162 0.0567 1.0000
15.750 1.3060 0.06564 0.05887 -0.0161 0.0550 1.0000
16.000 1.3143 0.06774 0.06101 -0.0160 0.0534 1.0000
16.250 1.3267 0.06942 0.06267 -0.0158 0.0518 1.0000
16.500 1.3376 0.07154 0.06488 -0.0154 0.0504 1.0000
16.750 1.3380 0.07463 0.06819 -0.0158 0.0494 1.0000
17.000 1.3390 0.07773 0.07146 -0.0162 0.0482 1.0000
17.250 1.3401 0.08087 0.07475 -0.0167 0.0472 1.0000
17.500 1.3423 0.08395 0.07796 -0.0173 0.0463 1.0000
17.750 1.3458 0.08684 0.08094 -0.0178 0.0454 1.0000
18.000 1.3523 0.08941 0.08358 -0.0182 0.0445 1.0000
18.250 1.3644 0.09180 0.08600 -0.0180 0.0435 1.0000
18.500 1.3523 0.09682 0.09127 -0.0198 0.0432 1.0000
18.750 1.3384 0.10228 0.09698 -0.0220 0.0429 1.0000
19.000 1.3219 0.10830 0.10326 -0.0247 0.0426 1.0000
19.250 1.3039 0.11484 0.11005 -0.0279 0.0424 1.0000
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Polar data table (+)
Polar graphs
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