S4062-095-87 (s4062-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 500,000 Max Cl/Cd: 114.52 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4062-il-500000-n5.txt Download as CSV file: xf-s4062-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2782 0.08257 0.08007 -0.0614 0.9085 0.0065
-9.000 -0.2801 0.07815 0.07562 -0.0632 0.8982 0.0066
-8.750 -0.2825 0.07408 0.07153 -0.0649 0.8882 0.0065
-8.500 -0.2867 0.06992 0.06738 -0.0668 0.8785 0.0064
-8.250 -0.3027 0.06405 0.06150 -0.0691 0.8678 0.0066
-8.000 -0.3170 0.05750 0.05494 -0.0744 0.8577 0.0066
-7.750 -0.3658 0.02850 0.02498 -0.0971 0.8440 0.0062
-7.500 -0.3503 0.02419 0.02008 -0.0985 0.8388 0.0063
-7.250 -0.3287 0.02192 0.01741 -0.0990 0.8339 0.0065
-7.000 -0.3055 0.02017 0.01528 -0.0992 0.8297 0.0067
-6.750 -0.2817 0.01839 0.01316 -0.0993 0.8255 0.0067
-6.500 -0.2575 0.01659 0.01104 -0.0993 0.8209 0.0068
-6.250 -0.2323 0.01529 0.00950 -0.0993 0.8167 0.0070
-6.000 -0.2063 0.01436 0.00840 -0.0992 0.8131 0.0073
-5.750 -0.1794 0.01360 0.00753 -0.0993 0.8087 0.0075
-5.500 -0.1524 0.01297 0.00677 -0.0993 0.8044 0.0078
-5.250 -0.1253 0.01240 0.00609 -0.0992 0.8006 0.0082
-5.000 -0.0979 0.01189 0.00547 -0.0992 0.7967 0.0087
-4.750 -0.0702 0.01144 0.00493 -0.0993 0.7923 0.0091
-4.500 -0.0424 0.01105 0.00444 -0.0993 0.7882 0.0096
-4.250 -0.0148 0.01062 0.00392 -0.0993 0.7845 0.0106
-4.000 0.0132 0.01033 0.00359 -0.0993 0.7803 0.0121
-3.750 0.0413 0.01004 0.00324 -0.0994 0.7759 0.0136
-3.500 0.0693 0.00974 0.00289 -0.0994 0.7720 0.0173
-3.250 0.0973 0.00945 0.00262 -0.0994 0.7682 0.0280
-3.000 0.1254 0.00920 0.00242 -0.0995 0.7637 0.0450
-2.750 0.1535 0.00899 0.00225 -0.0996 0.7595 0.0644
-2.500 0.1815 0.00880 0.00211 -0.0997 0.7556 0.0882
-2.250 0.2097 0.00860 0.00200 -0.0998 0.7513 0.1164
-2.000 0.2378 0.00844 0.00191 -0.0999 0.7468 0.1433
-1.750 0.2660 0.00831 0.00181 -0.1000 0.7427 0.1679
-1.500 0.2941 0.00818 0.00173 -0.1001 0.7386 0.1964
-1.250 0.3224 0.00804 0.00168 -0.1002 0.7339 0.2299
-1.000 0.3505 0.00792 0.00163 -0.1003 0.7293 0.2651
-0.750 0.3785 0.00780 0.00159 -0.1004 0.7251 0.3074
-0.500 0.4066 0.00766 0.00158 -0.1005 0.7199 0.3556
-0.250 0.4344 0.00750 0.00157 -0.1006 0.7146 0.4152
0.000 0.4621 0.00735 0.00157 -0.1006 0.7091 0.4801
0.250 0.4895 0.00717 0.00158 -0.1005 0.7013 0.5541
0.500 0.5162 0.00697 0.00161 -0.1003 0.6929 0.6398
0.750 0.5416 0.00674 0.00164 -0.0997 0.6835 0.7405
1.000 0.5635 0.00646 0.00169 -0.0981 0.6744 0.8613
1.250 0.5995 0.00632 0.00164 -0.0996 0.6654 1.0000
1.500 0.6272 0.00640 0.00167 -0.0996 0.6564 1.0000
1.750 0.6549 0.00648 0.00170 -0.0995 0.6474 1.0000
2.000 0.6824 0.00657 0.00174 -0.0994 0.6376 1.0000
2.250 0.7098 0.00667 0.00179 -0.0993 0.6266 1.0000
2.500 0.7372 0.00677 0.00186 -0.0993 0.6152 1.0000
2.750 0.7644 0.00689 0.00193 -0.0991 0.6026 1.0000
3.000 0.7913 0.00702 0.00202 -0.0990 0.5880 1.0000
3.250 0.8179 0.00718 0.00212 -0.0988 0.5711 1.0000
3.500 0.8440 0.00737 0.00223 -0.0985 0.5510 1.0000
3.750 0.8695 0.00762 0.00237 -0.0981 0.5247 1.0000
4.000 0.8943 0.00792 0.00256 -0.0976 0.4943 1.0000
4.250 0.9181 0.00830 0.00278 -0.0970 0.4569 1.0000
4.500 0.9410 0.00876 0.00305 -0.0963 0.4162 1.0000
5.000 0.9863 0.00973 0.00369 -0.0949 0.3426 1.0000
5.250 1.0090 0.01020 0.00402 -0.0942 0.3109 1.0000
5.500 1.0313 0.01069 0.00436 -0.0934 0.2799 1.0000
6.000 1.0751 0.01169 0.00510 -0.0918 0.2226 1.0000
6.250 1.0979 0.01210 0.00545 -0.0912 0.2053 1.0000
6.500 1.1200 0.01254 0.00581 -0.0904 0.1855 1.0000
6.750 1.1408 0.01307 0.00624 -0.0895 0.1630 1.0000
7.000 1.1617 0.01357 0.00666 -0.0885 0.1426 1.0000
7.250 1.1820 0.01409 0.00710 -0.0875 0.1241 1.0000
7.500 1.2014 0.01466 0.00758 -0.0863 0.1056 1.0000
7.750 1.2202 0.01524 0.00808 -0.0851 0.0886 1.0000
8.000 1.2379 0.01587 0.00864 -0.0837 0.0727 1.0000
8.250 1.2559 0.01644 0.00917 -0.0824 0.0617 1.0000
8.500 1.2724 0.01700 0.00972 -0.0807 0.0527 1.0000
8.750 1.2874 0.01759 0.01030 -0.0789 0.0451 1.0000
9.000 1.3016 0.01825 0.01094 -0.0769 0.0379 1.0000
9.250 1.3152 0.01896 0.01164 -0.0750 0.0309 1.0000
9.500 1.3287 0.01971 0.01240 -0.0731 0.0242 1.0000
9.750 1.3417 0.02051 0.01320 -0.0713 0.0191 1.0000
10.000 1.3544 0.02136 0.01407 -0.0695 0.0159 1.0000
10.250 1.3671 0.02223 0.01497 -0.0678 0.0142 1.0000
10.500 1.3792 0.02318 0.01597 -0.0660 0.0129 1.0000
10.750 1.3920 0.02409 0.01697 -0.0645 0.0122 1.0000
11.000 1.4042 0.02506 0.01803 -0.0629 0.0116 1.0000
11.250 1.4156 0.02612 0.01917 -0.0613 0.0111 1.0000
11.500 1.4257 0.02731 0.02043 -0.0598 0.0105 1.0000
11.750 1.4345 0.02863 0.02183 -0.0582 0.0099 1.0000
12.000 1.4406 0.03021 0.02351 -0.0564 0.0095 1.0000
12.250 1.4490 0.03163 0.02503 -0.0550 0.0092 1.0000
12.500 1.4568 0.03313 0.02663 -0.0536 0.0091 1.0000
12.750 1.4638 0.03473 0.02836 -0.0523 0.0088 1.0000
13.000 1.4698 0.03648 0.03022 -0.0511 0.0086 1.0000
13.250 1.4751 0.03834 0.03218 -0.0499 0.0083 1.0000
13.500 1.4792 0.04036 0.03431 -0.0489 0.0081 1.0000
13.750 1.4835 0.04242 0.03647 -0.0480 0.0078 1.0000
14.000 1.4865 0.04468 0.03884 -0.0472 0.0075 1.0000
14.250 1.4879 0.04716 0.04143 -0.0465 0.0073 1.0000
14.500 1.4876 0.04996 0.04434 -0.0460 0.0071 1.0000
14.750 1.4846 0.05322 0.04771 -0.0457 0.0070 1.0000
15.000 1.4769 0.05720 0.05183 -0.0456 0.0067 1.0000
15.250 1.4705 0.06122 0.05598 -0.0459 0.0066 1.0000
15.500 1.4716 0.06437 0.05926 -0.0463 0.0065 1.0000
15.750 1.4689 0.06817 0.06320 -0.0469 0.0064 1.0000
16.000 1.4673 0.07194 0.06714 -0.0478 0.0062 1.0000
16.250 1.4618 0.07646 0.07180 -0.0490 0.0061 1.0000
16.500 1.4565 0.08112 0.07661 -0.0505 0.0060 1.0000
16.750 1.4500 0.08613 0.08176 -0.0523 0.0058 1.0000
17.000 1.4411 0.09173 0.08751 -0.0545 0.0057 1.0000
17.250 1.4320 0.09758 0.09351 -0.0570 0.0056 1.0000
17.500 1.4222 0.10372 0.09980 -0.0599 0.0055 1.0000
17.750 1.4108 0.11032 0.10654 -0.0631 0.0055 1.0000
18.000 1.3999 0.11699 0.11335 -0.0665 0.0054 1.0000
18.250 1.3884 0.12393 0.12043 -0.0702 0.0053 1.0000
18.500 1.3768 0.13100 0.12764 -0.0741 0.0053 1.0000
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Polar data table (+)
Polar graphs
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