SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8040 (10%) (sd8040-il) Reynolds number: 100,000 Max Cl/Cd: 51.5 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8040-il-100000.txt Download as CSV file: xf-sd8040-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD8040 (10%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3893 0.10719 0.10201 -0.0239 1.0000 0.0983
-9.250 -0.3973 0.10468 0.09959 -0.0273 1.0000 0.1023
-9.000 -0.4242 0.10299 0.09805 -0.0341 1.0000 0.1037
-8.750 -0.3952 0.09725 0.09227 -0.0295 1.0000 0.1060
-8.500 -0.3823 0.09421 0.08924 -0.0282 1.0000 0.1095
-8.250 -0.3818 0.09136 0.08645 -0.0291 1.0000 0.1137
-8.000 -0.4069 0.08925 0.08450 -0.0331 1.0000 0.1175
-7.750 -0.4465 0.08662 0.08199 -0.0406 1.0000 0.1184
-7.500 -0.4082 0.08256 0.07797 -0.0312 1.0000 0.1215
-7.250 -0.4039 0.08018 0.07564 -0.0292 1.0000 0.1247
-7.000 -0.4126 0.07755 0.07310 -0.0296 1.0000 0.1286
-6.750 -0.4592 0.07416 0.06959 -0.0384 1.0000 0.1339
-6.500 -0.4420 0.07077 0.06641 -0.0328 1.0000 0.1359
-6.250 -0.4357 0.06884 0.06454 -0.0292 1.0000 0.1395
-6.000 -0.4546 0.06518 0.06063 -0.0347 1.0000 0.1497
-5.750 -0.4432 0.06277 0.05844 -0.0295 1.0000 0.1529
-5.500 -0.4460 0.05970 0.05515 -0.0321 1.0000 0.1657
-5.250 -0.4367 0.05749 0.05312 -0.0280 1.0000 0.1697
-5.000 -0.4319 0.05449 0.04999 -0.0288 1.0000 0.1831
-4.750 -0.3988 0.03656 0.03015 -0.0384 1.0000 0.0797
-4.500 -0.3778 0.03274 0.02576 -0.0379 1.0000 0.0721
-4.250 -0.3554 0.02940 0.02184 -0.0374 1.0000 0.0687
-4.000 -0.3314 0.02695 0.01879 -0.0368 1.0000 0.0675
-3.750 -0.3091 0.02554 0.01719 -0.0361 1.0000 0.0698
-3.500 -0.2865 0.02437 0.01574 -0.0354 1.0000 0.0735
-3.250 -0.2633 0.02327 0.01431 -0.0345 1.0000 0.0761
-3.000 -0.2410 0.02185 0.01290 -0.0338 1.0000 0.0804
-2.750 -0.2044 0.02096 0.01195 -0.0357 0.9955 0.0917
-2.500 -0.1615 0.01999 0.01114 -0.0387 0.9880 0.1131
-2.250 -0.1195 0.01894 0.01039 -0.0416 0.9803 0.1661
-2.000 -0.0799 0.01717 0.01004 -0.0447 0.9734 0.4025
-1.750 -0.0526 0.01628 0.01041 -0.0435 0.9637 0.7077
-1.500 0.0137 0.01599 0.01046 -0.0487 0.9594 1.0000
-1.250 0.0564 0.01615 0.01031 -0.0520 0.9475 1.0000
-1.000 0.0988 0.01631 0.01021 -0.0551 0.9359 1.0000
-0.750 0.1457 0.01644 0.01012 -0.0589 0.9256 1.0000
-0.500 0.1948 0.01646 0.00995 -0.0629 0.9156 1.0000
-0.250 0.2354 0.01646 0.00982 -0.0652 0.9031 1.0000
0.000 0.2803 0.01638 0.00961 -0.0681 0.8922 1.0000
0.250 0.3282 0.01615 0.00928 -0.0713 0.8828 1.0000
0.500 0.3619 0.01602 0.00908 -0.0719 0.8689 1.0000
0.750 0.3950 0.01587 0.00886 -0.0722 0.8551 1.0000
1.000 0.4272 0.01568 0.00861 -0.0722 0.8412 1.0000
1.250 0.4584 0.01547 0.00835 -0.0719 0.8269 1.0000
1.500 0.4881 0.01526 0.00808 -0.0713 0.8119 1.0000
1.750 0.5164 0.01507 0.00784 -0.0704 0.7959 1.0000
2.000 0.5438 0.01491 0.00762 -0.0694 0.7788 1.0000
2.250 0.5708 0.01477 0.00742 -0.0683 0.7608 1.0000
2.500 0.5978 0.01466 0.00723 -0.0672 0.7423 1.0000
2.750 0.6249 0.01458 0.00706 -0.0661 0.7233 1.0000
3.000 0.6491 0.01466 0.00709 -0.0648 0.7003 1.0000
3.250 0.6749 0.01471 0.00704 -0.0637 0.6785 1.0000
3.500 0.6999 0.01484 0.00709 -0.0625 0.6552 1.0000
3.750 0.7249 0.01501 0.00717 -0.0614 0.6313 1.0000
4.000 0.7494 0.01523 0.00729 -0.0603 0.6068 1.0000
4.250 0.7740 0.01547 0.00742 -0.0592 0.5823 1.0000
4.500 0.7978 0.01578 0.00767 -0.0581 0.5566 1.0000
4.750 0.8222 0.01610 0.00784 -0.0571 0.5323 1.0000
5.000 0.8453 0.01647 0.00816 -0.0560 0.5060 1.0000
5.250 0.8688 0.01688 0.00846 -0.0550 0.4810 1.0000
5.500 0.8919 0.01732 0.00881 -0.0539 0.4561 1.0000
5.750 0.9145 0.01779 0.00923 -0.0529 0.4310 1.0000
6.000 0.9374 0.01831 0.00961 -0.0519 0.4074 1.0000
6.250 0.9593 0.01886 0.01014 -0.0508 0.3827 1.0000
6.500 0.9817 0.01946 0.01061 -0.0498 0.3603 1.0000
6.750 1.0030 0.02008 0.01122 -0.0487 0.3368 1.0000
7.000 1.0246 0.02075 0.01180 -0.0477 0.3153 1.0000
7.250 1.0456 0.02147 0.01248 -0.0466 0.2943 1.0000
7.500 1.0662 0.02222 0.01322 -0.0455 0.2737 1.0000
7.750 1.0866 0.02300 0.01393 -0.0444 0.2547 1.0000
8.000 1.1072 0.02388 0.01471 -0.0434 0.2369 1.0000
8.250 1.1266 0.02478 0.01562 -0.0422 0.2195 1.0000
8.500 1.1457 0.02572 0.01659 -0.0410 0.2032 1.0000
8.750 1.1644 0.02672 0.01759 -0.0398 0.1879 1.0000
9.000 1.1830 0.02780 0.01868 -0.0386 0.1738 1.0000
9.250 1.2014 0.02896 0.01982 -0.0374 0.1608 1.0000
9.500 1.2206 0.03023 0.02099 -0.0365 0.1486 1.0000
9.750 1.2360 0.03139 0.02236 -0.0349 0.1376 1.0000
10.000 1.2523 0.03288 0.02399 -0.0335 0.1276 1.0000
10.250 1.2709 0.03450 0.02557 -0.0326 0.1190 1.0000
10.500 1.2859 0.03591 0.02711 -0.0311 0.1111 1.0000
10.750 1.3013 0.03789 0.02924 -0.0298 0.1044 1.0000
11.000 1.3158 0.03951 0.03099 -0.0284 0.0984 1.0000
11.250 1.3304 0.04182 0.03342 -0.0272 0.0933 1.0000
11.500 1.3376 0.04389 0.03582 -0.0251 0.0890 1.0000
11.750 1.3531 0.04581 0.03775 -0.0242 0.0850 1.0000
12.000 1.3581 0.04878 0.04097 -0.0223 0.0820 1.0000
12.250 1.3508 0.05132 0.04393 -0.0191 0.0799 1.0000
12.500 1.3435 0.05394 0.04685 -0.0161 0.0780 1.0000
12.750 1.3389 0.05667 0.04980 -0.0139 0.0762 1.0000
13.000 1.3362 0.05940 0.05268 -0.0122 0.0746 1.0000
13.250 1.3467 0.06320 0.05643 -0.0120 0.0721 1.0000
13.500 1.3229 0.06687 0.06042 -0.0100 0.0718 1.0000
13.750 1.2982 0.07132 0.06517 -0.0093 0.0717 1.0000
14.000 1.2714 0.07657 0.07068 -0.0097 0.0717 1.0000
14.250 1.2430 0.08270 0.07705 -0.0115 0.0718 1.0000
14.500 1.2144 0.08981 0.08436 -0.0144 0.0721 1.0000
14.750 0.9643 0.15318 0.14803 -0.0562 0.0953 1.0000
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Polar data table (+)
Polar graphs
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