SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 50,000 Max Cl/Cd: 36.31 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd5060-il-50000-n5.txt Download as CSV file: xf-sd5060-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4821 0.09493 0.08795 -0.0191 1.0000 0.0549
-9.000 -0.4838 0.09027 0.08336 -0.0217 1.0000 0.0551
-8.750 -0.4871 0.08534 0.07852 -0.0247 1.0000 0.0547
-8.500 -0.4932 0.07993 0.07321 -0.0283 1.0000 0.0542
-8.250 -0.5042 0.07333 0.06671 -0.0337 1.0000 0.0533
-8.000 -0.5183 0.06457 0.05792 -0.0415 1.0000 0.0522
-7.750 -0.5302 0.05707 0.05018 -0.0466 1.0000 0.0514
-7.500 -0.5319 0.05136 0.04412 -0.0492 1.0000 0.0513
-7.250 -0.5261 0.04689 0.03932 -0.0502 1.0000 0.0518
-7.000 -0.5162 0.04308 0.03514 -0.0505 1.0000 0.0525
-6.750 -0.5036 0.03973 0.03142 -0.0504 1.0000 0.0537
-6.500 -0.4890 0.03675 0.02804 -0.0498 1.0000 0.0553
-6.250 -0.4730 0.03420 0.02506 -0.0490 1.0000 0.0583
-6.000 -0.4558 0.03187 0.02226 -0.0480 1.0000 0.0620
-5.750 -0.4383 0.03034 0.02068 -0.0469 1.0000 0.0656
-5.500 -0.4198 0.02863 0.01873 -0.0456 1.0000 0.0695
-5.250 -0.4006 0.02696 0.01676 -0.0442 1.0000 0.0744
-5.000 -0.3826 0.02579 0.01560 -0.0429 1.0000 0.0819
-4.750 -0.3639 0.02471 0.01447 -0.0418 1.0000 0.0950
-4.500 -0.3444 0.02367 0.01332 -0.0406 1.0000 0.1145
-4.250 -0.3253 0.02296 0.01269 -0.0397 1.0000 0.1436
-4.000 -0.3061 0.02245 0.01228 -0.0389 1.0000 0.1782
-3.750 -0.2861 0.02191 0.01173 -0.0380 1.0000 0.2099
-3.500 -0.2661 0.02145 0.01124 -0.0371 1.0000 0.2389
-3.250 -0.2457 0.02106 0.01082 -0.0363 1.0000 0.2688
-3.000 -0.2107 0.02067 0.01043 -0.0382 0.9922 0.3071
-2.750 -0.1730 0.02031 0.01011 -0.0405 0.9834 0.3496
-2.500 -0.1372 0.01995 0.00983 -0.0424 0.9740 0.3966
-2.250 -0.1013 0.01962 0.00965 -0.0442 0.9649 0.4529
-2.000 -0.0650 0.01928 0.00956 -0.0458 0.9563 0.5240
-1.750 -0.0343 0.01894 0.00951 -0.0461 0.9460 0.6059
-1.500 -0.0041 0.01863 0.00953 -0.0457 0.9366 0.7080
-1.250 0.0363 0.01834 0.00951 -0.0467 0.9290 0.8486
-1.000 0.0990 0.01819 0.00917 -0.0534 0.9216 1.0000
-0.750 0.1389 0.01834 0.00905 -0.0560 0.9117 1.0000
-0.500 0.1730 0.01850 0.00901 -0.0575 0.8998 1.0000
-0.250 0.2052 0.01867 0.00899 -0.0584 0.8875 1.0000
0.000 0.2369 0.01884 0.00902 -0.0592 0.8752 1.0000
0.250 0.2683 0.01900 0.00906 -0.0598 0.8630 1.0000
0.500 0.2995 0.01915 0.00910 -0.0603 0.8508 1.0000
0.750 0.3305 0.01928 0.00914 -0.0605 0.8386 1.0000
1.000 0.3590 0.01942 0.00922 -0.0603 0.8252 1.0000
1.250 0.3862 0.01957 0.00931 -0.0598 0.8111 1.0000
1.500 0.4133 0.01970 0.00940 -0.0593 0.7966 1.0000
1.750 0.4404 0.01982 0.00948 -0.0586 0.7818 1.0000
2.000 0.4672 0.01991 0.00955 -0.0578 0.7666 1.0000
2.250 0.4933 0.01999 0.00961 -0.0569 0.7505 1.0000
2.500 0.5181 0.02010 0.00973 -0.0558 0.7326 1.0000
2.750 0.5433 0.02018 0.00983 -0.0546 0.7143 1.0000
3.000 0.5690 0.02022 0.00986 -0.0534 0.6959 1.0000
3.250 0.5945 0.02025 0.00988 -0.0522 0.6768 1.0000
3.500 0.6187 0.02036 0.01004 -0.0509 0.6548 1.0000
3.750 0.6440 0.02039 0.01006 -0.0496 0.6335 1.0000
4.000 0.6679 0.02053 0.01022 -0.0483 0.6087 1.0000
4.250 0.6920 0.02067 0.01036 -0.0470 0.5827 1.0000
4.500 0.7159 0.02084 0.01054 -0.0457 0.5549 1.0000
4.750 0.7395 0.02106 0.01074 -0.0443 0.5250 1.0000
5.000 0.7625 0.02136 0.01098 -0.0430 0.4932 1.0000
5.250 0.7852 0.02173 0.01127 -0.0417 0.4605 1.0000
5.500 0.8071 0.02223 0.01173 -0.0404 0.4264 1.0000
5.750 0.8287 0.02283 0.01223 -0.0392 0.3929 1.0000
6.000 0.8497 0.02352 0.01282 -0.0381 0.3612 1.0000
6.250 0.8706 0.02432 0.01352 -0.0370 0.3321 1.0000
6.500 0.8913 0.02518 0.01433 -0.0360 0.3060 1.0000
6.750 0.9120 0.02611 0.01521 -0.0350 0.2832 1.0000
7.000 0.9329 0.02709 0.01620 -0.0342 0.2623 1.0000
7.250 0.9536 0.02811 0.01719 -0.0333 0.2441 1.0000
7.500 0.9747 0.02917 0.01825 -0.0324 0.2282 1.0000
7.750 0.9955 0.03028 0.01936 -0.0316 0.2132 1.0000
8.000 1.0162 0.03142 0.02062 -0.0308 0.1993 1.0000
8.250 1.0366 0.03263 0.02196 -0.0299 0.1864 1.0000
8.500 1.0561 0.03390 0.02337 -0.0291 0.1739 1.0000
8.750 1.0755 0.03527 0.02490 -0.0282 0.1628 1.0000
9.000 1.0936 0.03666 0.02641 -0.0272 0.1522 1.0000
9.250 1.1119 0.03802 0.02780 -0.0263 0.1427 1.0000
9.500 1.1273 0.03971 0.02983 -0.0252 0.1328 1.0000
9.750 1.1417 0.04142 0.03173 -0.0241 0.1239 1.0000
10.000 1.1569 0.04297 0.03331 -0.0231 0.1162 1.0000
10.250 1.1661 0.04519 0.03593 -0.0217 0.1082 1.0000
10.500 1.1784 0.04682 0.03753 -0.0205 0.1015 1.0000
10.750 1.1821 0.04960 0.04079 -0.0189 0.0955 1.0000
11.000 1.1912 0.05127 0.04245 -0.0177 0.0899 1.0000
11.250 1.1855 0.05431 0.04593 -0.0158 0.0856 1.0000
11.500 1.1793 0.05734 0.04925 -0.0143 0.0819 1.0000
11.750 1.1803 0.05967 0.05165 -0.0132 0.0782 1.0000
12.000 1.1736 0.06304 0.05518 -0.0126 0.0754 1.0000
12.250 1.1535 0.06802 0.06052 -0.0130 0.0740 1.0000
12.500 1.1311 0.07379 0.06657 -0.0147 0.0731 1.0000
12.750 1.1046 0.08084 0.07387 -0.0178 0.0730 1.0000
13.000 1.0732 0.08967 0.08289 -0.0227 0.0737 1.0000
13.250 1.0381 0.10055 0.09384 -0.0294 0.0749 1.0000
13.500 1.0018 0.11333 0.10666 -0.0374 0.0758 1.0000
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Polar data table (+)
Polar graphs
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