SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 50,000 Max Cl/Cd: 36.09 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6080-il-50000.txt Download as CSV file: xf-sd6080-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3457 0.10530 0.09886 -0.0273 1.0000 0.1955
-8.000 -0.3247 0.09986 0.09342 -0.0258 1.0000 0.2036
-7.750 -0.3427 0.09981 0.09356 -0.0271 1.0000 0.2103
-7.500 -0.3220 0.09473 0.08849 -0.0256 1.0000 0.2191
-7.250 -0.3457 0.09500 0.08899 -0.0253 1.0000 0.2251
-7.000 -0.3279 0.09045 0.08447 -0.0235 1.0000 0.2349
-6.750 -0.3600 0.09118 0.08545 -0.0223 1.0000 0.2401
-6.500 -0.3461 0.08716 0.08145 -0.0190 1.0000 0.2496
-6.250 -0.3791 0.08788 0.08240 -0.0181 1.0000 0.2552
-6.000 -0.3690 0.08422 0.07877 -0.0138 1.0000 0.2650
-5.750 -0.3911 0.08345 0.07815 -0.0127 1.0000 0.2723
-5.500 -0.3979 0.08185 0.07661 -0.0103 1.0000 0.2842
-5.250 -0.3977 0.07922 0.07406 -0.0068 1.0000 0.2946
-5.000 -0.4043 0.07723 0.07215 -0.0048 1.0000 0.3069
-4.750 -0.4090 0.07517 0.07016 -0.0026 1.0000 0.3225
-4.500 -0.4149 0.07349 0.06855 -0.0014 1.0000 0.3437
-4.250 -0.4159 0.07104 0.06617 0.0020 1.0000 0.3645
-4.000 -0.4188 0.06923 0.06441 0.0040 1.0000 0.3921
-3.750 -0.4188 0.06697 0.06223 0.0098 1.0000 0.4244
-3.250 -0.2608 0.04402 0.03661 -0.0477 1.0000 0.1363
-3.000 -0.2356 0.04052 0.03287 -0.0487 1.0000 0.1288
-2.750 -0.2031 0.03718 0.02871 -0.0505 1.0000 0.1198
-2.500 -0.1758 0.03472 0.02574 -0.0512 1.0000 0.1179
-2.250 -0.1489 0.03292 0.02336 -0.0514 1.0000 0.1210
-2.000 -0.1252 0.03137 0.02165 -0.0514 1.0000 0.1287
-1.750 -0.0992 0.03015 0.01990 -0.0511 1.0000 0.1369
-1.500 -0.0763 0.02899 0.01879 -0.0508 1.0000 0.1562
-1.250 -0.0525 0.02805 0.01781 -0.0504 1.0000 0.1937
-1.000 -0.0244 0.02686 0.01695 -0.0506 1.0000 0.2816
-0.750 0.0083 0.02344 0.01596 -0.0496 0.9954 1.0000
-0.500 0.0529 0.02451 0.01621 -0.0537 0.9854 1.0000
-0.250 0.0920 0.02546 0.01663 -0.0570 0.9752 1.0000
0.000 0.1291 0.02642 0.01720 -0.0599 0.9648 1.0000
0.250 0.1672 0.02743 0.01787 -0.0630 0.9545 1.0000
0.500 0.2082 0.02851 0.01864 -0.0665 0.9441 1.0000
0.750 0.2378 0.02936 0.01928 -0.0680 0.9328 1.0000
1.000 0.2690 0.03029 0.02002 -0.0697 0.9218 1.0000
1.250 0.3027 0.03128 0.02084 -0.0718 0.9108 1.0000
1.500 0.3409 0.03232 0.02173 -0.0746 0.8997 1.0000
1.750 0.3688 0.03323 0.02255 -0.0756 0.8877 1.0000
2.000 0.3955 0.03417 0.02342 -0.0765 0.8754 1.0000
2.250 0.4239 0.03516 0.02433 -0.0775 0.8632 1.0000
2.500 0.4540 0.03615 0.02529 -0.0787 0.8507 1.0000
2.750 0.4858 0.03713 0.02624 -0.0801 0.8379 1.0000
3.000 0.5187 0.03807 0.02718 -0.0815 0.8248 1.0000
3.250 0.5533 0.03896 0.02808 -0.0830 0.8116 1.0000
3.500 0.5820 0.03986 0.02902 -0.0836 0.7977 1.0000
3.750 0.6101 0.04075 0.02998 -0.0840 0.7832 1.0000
4.000 0.6392 0.04160 0.03089 -0.0845 0.7685 1.0000
4.250 0.6697 0.04237 0.03173 -0.0849 0.7536 1.0000
4.500 0.6979 0.04313 0.03258 -0.0850 0.7380 1.0000
4.750 0.7177 0.04412 0.03369 -0.0841 0.7211 1.0000
5.000 0.7416 0.04495 0.03463 -0.0836 0.7040 1.0000
5.250 0.7704 0.04553 0.03534 -0.0833 0.6868 1.0000
5.500 0.8057 0.04566 0.03564 -0.0832 0.6697 1.0000
5.750 0.8498 0.04510 0.03533 -0.0833 0.6530 1.0000
6.000 0.8958 0.04391 0.03438 -0.0827 0.6369 1.0000
6.250 0.9080 0.04499 0.03560 -0.0806 0.6155 1.0000
6.500 0.9498 0.04360 0.03450 -0.0792 0.5973 1.0000
6.750 1.0037 0.04081 0.03199 -0.0777 0.5796 1.0000
7.000 1.0295 0.04034 0.03172 -0.0754 0.5564 1.0000
7.250 1.0851 0.03692 0.02855 -0.0736 0.5337 1.0000
7.500 1.1242 0.03497 0.02673 -0.0714 0.5058 1.0000
7.750 1.1495 0.03436 0.02626 -0.0688 0.4741 1.0000
8.000 1.1754 0.03379 0.02573 -0.0663 0.4395 1.0000
8.250 1.2020 0.03337 0.02518 -0.0639 0.4027 1.0000
8.500 1.2208 0.03383 0.02556 -0.0614 0.3651 1.0000
8.750 1.2372 0.03476 0.02639 -0.0589 0.3282 1.0000
9.000 1.2538 0.03589 0.02726 -0.0566 0.2912 1.0000
9.250 1.2640 0.03765 0.02897 -0.0539 0.2567 1.0000
9.500 1.2737 0.03945 0.03053 -0.0513 0.2215 1.0000
9.750 1.2761 0.04130 0.03218 -0.0483 0.1890 1.0000
10.000 1.2754 0.04337 0.03412 -0.0452 0.1609 1.0000
10.250 1.2811 0.04603 0.03657 -0.0429 0.1355 1.0000
10.500 1.2886 0.04935 0.04013 -0.0406 0.1184 1.0000
10.750 1.2993 0.05274 0.04364 -0.0390 0.1065 1.0000
11.000 1.3158 0.05625 0.04712 -0.0381 0.0968 1.0000
11.250 1.3112 0.06007 0.05151 -0.0355 0.0941 1.0000
11.500 1.3043 0.06398 0.05584 -0.0330 0.0921 1.0000
11.750 1.2933 0.06796 0.06017 -0.0308 0.0909 1.0000
12.000 1.2773 0.07220 0.06473 -0.0290 0.0904 1.0000
12.250 1.2555 0.07690 0.06973 -0.0280 0.0907 1.0000
12.500 1.2290 0.08229 0.07539 -0.0282 0.0914 1.0000
12.750 1.2001 0.08853 0.08187 -0.0297 0.0925 1.0000
13.000 1.1705 0.09565 0.08917 -0.0324 0.0939 1.0000
13.250 1.1423 0.10358 0.09722 -0.0362 0.0952 1.0000
13.500 1.1175 0.11204 0.10575 -0.0405 0.0964 1.0000
13.750 1.0984 0.12062 0.11436 -0.0448 0.0973 1.0000
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Polar data table (+)
Polar graphs
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