S4062-095-87 (s4062-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 50,000 Max Cl/Cd: 38.41 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4062-il-50000-n5.txt Download as CSV file: xf-s4062-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4062-095-87
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3208 0.10371 0.09708 -0.0417 1.0000 0.0586
-8.500 -0.3261 0.10144 0.09492 -0.0403 1.0000 0.0560
-8.000 -0.3703 0.09779 0.09157 -0.0382 1.0000 0.0494
-7.750 -0.3749 0.09598 0.08983 -0.0353 1.0000 0.0486
-7.500 -0.3868 0.09439 0.08833 -0.0327 1.0000 0.0480
-7.250 -0.3988 0.09269 0.08673 -0.0305 1.0000 0.0474
-7.000 -0.4074 0.09028 0.08437 -0.0298 0.9995 0.0467
-6.750 -0.3932 0.08531 0.07939 -0.0358 0.9921 0.0455
-6.500 -0.3774 0.07993 0.07399 -0.0427 0.9849 0.0443
-6.250 -0.3626 0.07427 0.06828 -0.0496 0.9771 0.0432
-6.000 -0.3433 0.06763 0.06151 -0.0579 0.9704 0.0421
-5.750 -0.3249 0.06122 0.05489 -0.0648 0.9633 0.0417
-5.500 -0.2998 0.05546 0.04883 -0.0713 0.9579 0.0424
-5.250 -0.2787 0.05065 0.04366 -0.0754 0.9511 0.0439
-5.000 -0.2488 0.04549 0.03793 -0.0804 0.9464 0.0454
-4.750 -0.2213 0.04115 0.03294 -0.0833 0.9414 0.0465
-4.500 -0.1919 0.03730 0.02833 -0.0854 0.9364 0.0480
-4.250 -0.1587 0.03438 0.02477 -0.0874 0.9327 0.0509
-4.000 -0.1297 0.03296 0.02310 -0.0884 0.9282 0.0571
-3.750 -0.1019 0.03119 0.02088 -0.0886 0.9230 0.0634
-3.500 -0.0699 0.02995 0.01940 -0.0897 0.9189 0.0762
-3.250 -0.0371 0.02892 0.01829 -0.0909 0.9153 0.0952
-3.000 -0.0133 0.02814 0.01736 -0.0904 0.9092 0.1192
-2.750 0.0183 0.02747 0.01665 -0.0914 0.9048 0.1539
-2.500 0.0542 0.02687 0.01604 -0.0932 0.9016 0.2000
-2.250 0.0756 0.02652 0.01574 -0.0924 0.8949 0.2416
-2.000 0.1068 0.02609 0.01544 -0.0934 0.8903 0.3035
-1.750 0.1410 0.02562 0.01525 -0.0948 0.8870 0.3908
-1.500 0.1587 0.02531 0.01529 -0.0932 0.8799 0.4874
-1.250 0.1814 0.02471 0.01532 -0.0915 0.8752 0.6578
-1.000 0.2229 0.02421 0.01506 -0.0931 0.8720 1.0000
-0.750 0.2416 0.02460 0.01513 -0.0920 0.8640 1.0000
-0.500 0.2749 0.02491 0.01511 -0.0933 0.8593 1.0000
-0.250 0.2984 0.02531 0.01525 -0.0930 0.8526 1.0000
0.250 0.3626 0.02597 0.01547 -0.0950 0.8427 1.0000
0.500 0.3787 0.02648 0.01582 -0.0934 0.8338 1.0000
0.750 0.4128 0.02678 0.01597 -0.0946 0.8291 1.0000
1.000 0.4318 0.02729 0.01636 -0.0936 0.8208 1.0000
1.250 0.4640 0.02760 0.01656 -0.0944 0.8153 1.0000
1.500 0.4851 0.02809 0.01697 -0.0936 0.8071 1.0000
1.750 0.5163 0.02838 0.01720 -0.0943 0.8009 1.0000
2.000 0.5379 0.02886 0.01763 -0.0935 0.7922 1.0000
2.250 0.5701 0.02908 0.01783 -0.0941 0.7859 1.0000
2.500 0.5909 0.02955 0.01829 -0.0932 0.7761 1.0000
2.750 0.6265 0.02957 0.01831 -0.0941 0.7702 1.0000
3.000 0.6462 0.03002 0.01880 -0.0929 0.7590 1.0000
3.250 0.6720 0.03026 0.01906 -0.0924 0.7495 1.0000
3.500 0.7053 0.03018 0.01902 -0.0927 0.7417 1.0000
3.750 0.7272 0.03045 0.01936 -0.0916 0.7298 1.0000
4.000 0.7523 0.03057 0.01957 -0.0908 0.7186 1.0000
4.250 0.7857 0.03027 0.01937 -0.0907 0.7096 1.0000
4.500 0.8132 0.03017 0.01936 -0.0900 0.6982 1.0000
4.750 0.8369 0.03020 0.01954 -0.0888 0.6850 1.0000
5.000 0.8617 0.03014 0.01960 -0.0877 0.6716 1.0000
5.250 0.8874 0.02998 0.01958 -0.0866 0.6577 1.0000
5.500 0.9135 0.02975 0.01954 -0.0854 0.6431 1.0000
5.750 0.9401 0.02943 0.01937 -0.0842 0.6275 1.0000
6.000 0.9679 0.02901 0.01911 -0.0831 0.6109 1.0000
6.250 0.9870 0.02907 0.01933 -0.0811 0.5896 1.0000
6.500 1.0131 0.02870 0.01913 -0.0797 0.5682 1.0000
6.750 1.0340 0.02866 0.01923 -0.0778 0.5420 1.0000
7.000 1.0576 0.02850 0.01915 -0.0762 0.5126 1.0000
7.250 1.0819 0.02837 0.01902 -0.0745 0.4794 1.0000
7.500 1.1011 0.02867 0.01932 -0.0725 0.4430 1.0000
7.750 1.1195 0.02916 0.01965 -0.0705 0.4067 1.0000
8.000 1.1325 0.03002 0.02041 -0.0682 0.3727 1.0000
8.250 1.1439 0.03108 0.02135 -0.0659 0.3418 1.0000
8.500 1.1538 0.03230 0.02248 -0.0636 0.3135 1.0000
8.750 1.1629 0.03362 0.02372 -0.0614 0.2874 1.0000
9.000 1.1714 0.03503 0.02513 -0.0593 0.2634 1.0000
9.250 1.1794 0.03653 0.02664 -0.0574 0.2403 1.0000
9.500 1.1868 0.03811 0.02818 -0.0555 0.2195 1.0000
9.750 1.1940 0.03979 0.02991 -0.0537 0.1990 1.0000
10.000 1.2007 0.04155 0.03170 -0.0520 0.1804 1.0000
10.250 1.2067 0.04344 0.03358 -0.0504 0.1635 1.0000
10.500 1.2130 0.04543 0.03559 -0.0489 0.1475 1.0000
10.750 1.2183 0.04755 0.03784 -0.0475 0.1321 1.0000
11.000 1.2233 0.04980 0.04014 -0.0462 0.1185 1.0000
11.250 1.2260 0.05221 0.04260 -0.0450 0.1064 1.0000
11.500 1.2278 0.05475 0.04515 -0.0439 0.0959 1.0000
11.750 1.2299 0.05748 0.04806 -0.0430 0.0856 1.0000
12.000 1.2332 0.06030 0.05105 -0.0421 0.0773 1.0000
12.250 1.2337 0.06317 0.05388 -0.0415 0.0712 1.0000
12.500 1.2373 0.06636 0.05742 -0.0407 0.0650 1.0000
12.750 1.2378 0.06944 0.06052 -0.0403 0.0607 1.0000
13.000 1.2391 0.07307 0.06448 -0.0399 0.0568 1.0000
13.250 1.2390 0.07696 0.06869 -0.0396 0.0540 1.0000
13.500 1.2367 0.08093 0.07287 -0.0397 0.0518 1.0000
13.750 1.2360 0.08459 0.07661 -0.0399 0.0498 1.0000
14.000 1.2296 0.08937 0.08158 -0.0407 0.0484 1.0000
14.250 1.2147 0.09548 0.08805 -0.0426 0.0476 1.0000
14.500 1.1980 0.10224 0.09512 -0.0453 0.0471 1.0000
14.750 1.1788 0.10988 0.10302 -0.0490 0.0469 1.0000
15.000 1.1576 0.11857 0.11194 -0.0538 0.0470 1.0000
15.250 1.1355 0.12832 0.12189 -0.0596 0.0474 1.0000
15.500 1.1128 0.13921 0.13291 -0.0664 0.0480 1.0000
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Polar data table (+)
Polar graphs
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