S4083 (8%) (s4083-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 50,000 Max Cl/Cd: 38.5 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4083-il-50000-n5.txt Download as CSV file: xf-s4083-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4083 (8%)
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3741 0.09834 0.09169 -0.0179 1.0000 0.1058
-7.250 -0.3866 0.09710 0.09062 -0.0207 1.0000 0.1099
-7.000 -0.3897 0.09468 0.08835 -0.0260 1.0000 0.1108
-6.750 -0.3786 0.09015 0.08385 -0.0228 1.0000 0.1122
-6.500 -0.3709 0.08664 0.08040 -0.0223 1.0000 0.1137
-6.000 -0.3483 0.07389 0.06756 -0.0368 1.0000 0.0562
-5.750 -0.3399 0.07110 0.06480 -0.0338 1.0000 0.0520
-5.500 -0.3289 0.06701 0.06072 -0.0360 1.0000 0.0493
-5.000 -0.2900 0.05551 0.04878 -0.0467 1.0000 0.0421
-4.750 -0.2738 0.05181 0.04500 -0.0479 1.0000 0.0414
-4.500 -0.2543 0.04786 0.04085 -0.0497 1.0000 0.0408
-4.250 -0.2319 0.04387 0.03654 -0.0518 1.0000 0.0408
-4.000 -0.2073 0.04010 0.03232 -0.0536 1.0000 0.0415
-3.750 -0.1816 0.03684 0.02851 -0.0547 1.0000 0.0424
-3.500 -0.1571 0.03391 0.02513 -0.0552 1.0000 0.0432
-3.250 -0.1329 0.03133 0.02220 -0.0554 1.0000 0.0439
-3.000 -0.1082 0.02912 0.01964 -0.0552 1.0000 0.0446
-2.750 -0.0838 0.02728 0.01749 -0.0548 1.0000 0.0459
-2.500 -0.0596 0.02575 0.01569 -0.0542 1.0000 0.0478
-2.250 -0.0357 0.02451 0.01419 -0.0534 1.0000 0.0517
-2.000 -0.0105 0.02344 0.01294 -0.0531 0.9985 0.0583
-1.750 0.0358 0.02215 0.01142 -0.0566 0.9843 0.0730
-1.500 0.0811 0.02087 0.01013 -0.0600 0.9680 0.1128
-1.250 0.1251 0.01879 0.00921 -0.0638 0.9527 0.3346
-1.000 0.1639 0.01657 0.00865 -0.0643 0.9342 1.0000
-0.750 0.2072 0.01655 0.00806 -0.0671 0.9107 1.0000
-0.500 0.2510 0.01652 0.00759 -0.0698 0.8870 1.0000
-0.250 0.2963 0.01649 0.00717 -0.0728 0.8625 1.0000
0.000 0.3400 0.01648 0.00681 -0.0754 0.8360 1.0000
0.250 0.3813 0.01651 0.00653 -0.0775 0.8077 1.0000
0.500 0.4194 0.01661 0.00630 -0.0789 0.7789 1.0000
0.750 0.4540 0.01679 0.00618 -0.0796 0.7509 1.0000
1.000 0.4852 0.01704 0.00616 -0.0798 0.7244 1.0000
1.250 0.5142 0.01733 0.00622 -0.0797 0.6997 1.0000
1.500 0.5426 0.01766 0.00631 -0.0794 0.6777 1.0000
1.750 0.5697 0.01801 0.00649 -0.0790 0.6568 1.0000
2.000 0.5970 0.01838 0.00668 -0.0786 0.6384 1.0000
2.250 0.6238 0.01876 0.00695 -0.0782 0.6208 1.0000
2.500 0.6506 0.01917 0.00726 -0.0779 0.6042 1.0000
2.750 0.6774 0.01958 0.00759 -0.0776 0.5885 1.0000
3.000 0.7042 0.02001 0.00797 -0.0773 0.5739 1.0000
3.250 0.7309 0.02045 0.00841 -0.0769 0.5598 1.0000
3.500 0.7574 0.02091 0.00884 -0.0766 0.5465 1.0000
3.750 0.7837 0.02137 0.00930 -0.0762 0.5336 1.0000
4.000 0.8098 0.02185 0.00978 -0.0758 0.5212 1.0000
4.250 0.8355 0.02233 0.01035 -0.0754 0.5089 1.0000
4.500 0.8605 0.02284 0.01093 -0.0748 0.4961 1.0000
4.750 0.8852 0.02337 0.01154 -0.0742 0.4835 1.0000
5.000 0.9097 0.02392 0.01218 -0.0735 0.4712 1.0000
5.250 0.9340 0.02447 0.01289 -0.0729 0.4591 1.0000
5.500 0.9583 0.02503 0.01356 -0.0722 0.4471 1.0000
5.750 0.9824 0.02559 0.01421 -0.0714 0.4352 1.0000
6.000 1.0064 0.02614 0.01488 -0.0706 0.4231 1.0000
6.250 1.0290 0.02675 0.01567 -0.0697 0.4100 1.0000
6.500 1.0514 0.02735 0.01650 -0.0687 0.3965 1.0000
6.750 1.0734 0.02795 0.01729 -0.0676 0.3828 1.0000
7.000 1.0950 0.02855 0.01809 -0.0665 0.3688 1.0000
7.250 1.1161 0.02914 0.01887 -0.0652 0.3543 1.0000
7.500 1.1368 0.02973 0.01965 -0.0639 0.3393 1.0000
7.750 1.1567 0.03031 0.02046 -0.0625 0.3236 1.0000
8.000 1.1744 0.03101 0.02145 -0.0609 0.3058 1.0000
8.250 1.1919 0.03166 0.02234 -0.0593 0.2878 1.0000
8.500 1.2088 0.03227 0.02310 -0.0575 0.2696 1.0000
8.750 1.2234 0.03311 0.02417 -0.0556 0.2494 1.0000
9.000 1.2362 0.03392 0.02511 -0.0534 0.2282 1.0000
9.250 1.2458 0.03499 0.02641 -0.0511 0.2044 1.0000
9.500 1.2522 0.03627 0.02775 -0.0487 0.1801 1.0000
9.750 1.2544 0.03789 0.02937 -0.0460 0.1561 1.0000
10.000 1.2523 0.03992 0.03137 -0.0433 0.1339 1.0000
10.250 1.2459 0.04226 0.03372 -0.0403 0.1149 1.0000
10.500 1.2361 0.04502 0.03648 -0.0376 0.0998 1.0000
10.750 1.2251 0.04819 0.03965 -0.0358 0.0878 1.0000
11.000 1.2134 0.05179 0.04326 -0.0350 0.0783 1.0000
11.250 1.2010 0.05592 0.04739 -0.0352 0.0705 1.0000
11.500 1.1914 0.06027 0.05188 -0.0359 0.0630 1.0000
11.750 1.1798 0.06502 0.05661 -0.0373 0.0583 1.0000
12.000 1.1724 0.06966 0.06146 -0.0384 0.0526 1.0000
12.250 1.1636 0.07447 0.06632 -0.0399 0.0489 1.0000
12.500 1.1558 0.07925 0.07115 -0.0412 0.0459 1.0000
12.750 1.1503 0.08400 0.07615 -0.0423 0.0431 1.0000
13.000 1.1441 0.08889 0.08121 -0.0437 0.0407 1.0000
13.250 1.1384 0.09373 0.08617 -0.0452 0.0390 1.0000
13.500 1.1332 0.09844 0.09094 -0.0467 0.0375 1.0000
13.750 1.1273 0.10353 0.09612 -0.0483 0.0362 1.0000
14.000 1.1181 0.10982 0.10268 -0.0511 0.0355 1.0000
14.250 1.1076 0.11659 0.10969 -0.0543 0.0352 1.0000
14.500 1.0951 0.12415 0.11745 -0.0582 0.0350 1.0000
14.750 1.0817 0.13238 0.12586 -0.0627 0.0351 1.0000
15.000 1.0671 0.14139 0.13500 -0.0678 0.0354 1.0000
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Polar data table (+)
Polar graphs
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