SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8040 (10%) (sd8040-il) Reynolds number: 50,000 Max Cl/Cd: 36.73 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8040-il-50000-n5.txt Download as CSV file: xf-sd8040-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4173 0.08724 0.08013 -0.0378 1.0000 0.0511
-8.250 -0.4181 0.08379 0.07677 -0.0385 1.0000 0.0506
-8.000 -0.4234 0.08012 0.07320 -0.0396 1.0000 0.0500
-7.750 -0.4287 0.07604 0.06920 -0.0416 1.0000 0.0494
-7.500 -0.4351 0.07179 0.06499 -0.0432 1.0000 0.0488
-7.250 -0.4419 0.06760 0.06080 -0.0442 1.0000 0.0482
-7.000 -0.4478 0.06346 0.05661 -0.0448 1.0000 0.0477
-6.750 -0.4523 0.05936 0.05239 -0.0451 1.0000 0.0475
-6.500 -0.4536 0.05541 0.04826 -0.0450 1.0000 0.0475
-6.250 -0.4515 0.05159 0.04418 -0.0448 1.0000 0.0479
-6.000 -0.4460 0.04785 0.04008 -0.0444 1.0000 0.0487
-5.750 -0.4369 0.04431 0.03612 -0.0439 1.0000 0.0494
-5.500 -0.4244 0.04099 0.03231 -0.0433 1.0000 0.0503
-5.250 -0.4090 0.03799 0.02879 -0.0425 1.0000 0.0509
-5.000 -0.3912 0.03531 0.02561 -0.0416 1.0000 0.0516
-4.750 -0.3730 0.03333 0.02345 -0.0408 1.0000 0.0528
-4.500 -0.3539 0.03179 0.02175 -0.0399 1.0000 0.0554
-4.250 -0.3334 0.03025 0.01989 -0.0389 1.0000 0.0591
-4.000 -0.3121 0.02871 0.01806 -0.0380 1.0000 0.0627
-3.750 -0.2915 0.02756 0.01684 -0.0370 1.0000 0.0666
-3.500 -0.2697 0.02649 0.01553 -0.0359 1.0000 0.0735
-3.250 -0.2453 0.02557 0.01460 -0.0357 0.9984 0.0821
-3.000 -0.2079 0.02460 0.01350 -0.0377 0.9911 0.0984
-2.750 -0.1700 0.02367 0.01264 -0.0400 0.9839 0.1259
-2.500 -0.1333 0.02265 0.01187 -0.0423 0.9757 0.1794
-2.250 -0.0978 0.02154 0.01139 -0.0445 0.9676 0.2948
-2.000 -0.0648 0.02050 0.01137 -0.0457 0.9596 0.5035
-1.750 -0.0419 0.01992 0.01151 -0.0434 0.9492 0.6982
-1.500 0.0060 0.01963 0.01148 -0.0450 0.9429 0.9159
-1.250 0.0601 0.01963 0.01109 -0.0504 0.9330 1.0000
-1.000 0.0968 0.01976 0.01090 -0.0525 0.9210 1.0000
-0.750 0.1364 0.01989 0.01075 -0.0550 0.9100 1.0000
-0.500 0.1766 0.01999 0.01060 -0.0574 0.8990 1.0000
-0.250 0.2100 0.02009 0.01051 -0.0585 0.8856 1.0000
0.000 0.2432 0.02017 0.01042 -0.0595 0.8724 1.0000
0.250 0.2770 0.02023 0.01033 -0.0604 0.8593 1.0000
0.500 0.3112 0.02024 0.01022 -0.0613 0.8464 1.0000
0.750 0.3456 0.02022 0.01008 -0.0621 0.8335 1.0000
1.000 0.3751 0.02024 0.01002 -0.0620 0.8184 1.0000
1.250 0.4046 0.02025 0.00995 -0.0618 0.8031 1.0000
1.500 0.4339 0.02025 0.00989 -0.0616 0.7875 1.0000
1.750 0.4630 0.02024 0.00982 -0.0612 0.7715 1.0000
2.000 0.4919 0.02023 0.00976 -0.0608 0.7550 1.0000
2.250 0.5207 0.02022 0.00970 -0.0602 0.7382 1.0000
2.500 0.5471 0.02029 0.00973 -0.0594 0.7194 1.0000
2.750 0.5736 0.02036 0.00977 -0.0586 0.7000 1.0000
3.000 0.6005 0.02043 0.00981 -0.0578 0.6805 1.0000
3.250 0.6278 0.02050 0.00983 -0.0569 0.6608 1.0000
3.500 0.6541 0.02063 0.00990 -0.0560 0.6402 1.0000
3.750 0.6790 0.02083 0.01010 -0.0550 0.6178 1.0000
4.000 0.7049 0.02102 0.01022 -0.0541 0.5963 1.0000
4.250 0.7294 0.02129 0.01046 -0.0531 0.5736 1.0000
4.500 0.7537 0.02159 0.01072 -0.0520 0.5507 1.0000
4.750 0.7780 0.02193 0.01101 -0.0510 0.5281 1.0000
5.000 0.8012 0.02233 0.01139 -0.0499 0.5046 1.0000
5.250 0.8250 0.02273 0.01171 -0.0489 0.4822 1.0000
5.500 0.8472 0.02322 0.01224 -0.0478 0.4586 1.0000
5.750 0.8700 0.02371 0.01267 -0.0467 0.4364 1.0000
6.000 0.8917 0.02428 0.01324 -0.0457 0.4137 1.0000
6.250 0.9134 0.02487 0.01381 -0.0446 0.3917 1.0000
6.500 0.9348 0.02550 0.01441 -0.0435 0.3707 1.0000
6.750 0.9553 0.02620 0.01515 -0.0423 0.3492 1.0000
7.000 0.9756 0.02693 0.01587 -0.0412 0.3290 1.0000
7.250 0.9956 0.02769 0.01662 -0.0400 0.3100 1.0000
7.500 1.0149 0.02853 0.01750 -0.0389 0.2910 1.0000
7.750 1.0336 0.02942 0.01844 -0.0377 0.2725 1.0000
8.000 1.0519 0.03035 0.01942 -0.0365 0.2554 1.0000
8.250 1.0694 0.03134 0.02046 -0.0352 0.2389 1.0000
8.500 1.0867 0.03239 0.02156 -0.0340 0.2236 1.0000
8.750 1.1028 0.03350 0.02272 -0.0326 0.2089 1.0000
9.000 1.1185 0.03469 0.02398 -0.0313 0.1953 1.0000
9.250 1.1331 0.03593 0.02530 -0.0299 0.1825 1.0000
9.500 1.1473 0.03722 0.02662 -0.0285 0.1710 1.0000
9.750 1.1600 0.03855 0.02800 -0.0270 0.1600 1.0000
10.000 1.1715 0.04012 0.02976 -0.0255 0.1495 1.0000
10.250 1.1819 0.04169 0.03145 -0.0239 0.1403 1.0000
10.500 1.1915 0.04318 0.03295 -0.0222 0.1323 1.0000
10.750 1.1975 0.04511 0.03513 -0.0204 0.1246 1.0000
11.000 1.2063 0.04667 0.03664 -0.0189 0.1182 1.0000
11.250 1.2086 0.04907 0.03937 -0.0171 0.1120 1.0000
11.500 1.2140 0.05097 0.04135 -0.0157 0.1066 1.0000
11.750 1.2155 0.05355 0.04414 -0.0144 0.1020 1.0000
12.000 1.2135 0.05644 0.04729 -0.0133 0.0978 1.0000
12.250 1.2171 0.05869 0.04958 -0.0124 0.0939 1.0000
12.500 1.2135 0.06196 0.05305 -0.0118 0.0908 1.0000
12.750 1.1995 0.06639 0.05783 -0.0118 0.0885 1.0000
13.000 1.1856 0.07112 0.06283 -0.0125 0.0866 1.0000
13.250 1.1709 0.07625 0.06818 -0.0139 0.0849 1.0000
13.500 1.1577 0.08143 0.07352 -0.0156 0.0833 1.0000
13.750 1.1637 0.08395 0.07600 -0.0157 0.0805 1.0000
14.000 1.1327 0.09251 0.08482 -0.0201 0.0804 1.0000
14.250 1.0962 0.10316 0.09568 -0.0264 0.0806 1.0000
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Polar data table (+)
Polar graphs
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