S4061-096-84 (s4061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.22 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4061-il-1000000-n5.txt Download as CSV file: xf-s4061-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3380 0.09680 0.09497 -0.0377 0.9182 0.0050
-9.000 -0.5612 0.02585 0.02277 -0.0809 0.8325 0.0043
-8.500 -0.5228 0.02088 0.01714 -0.0821 0.8188 0.0044
-8.250 -0.5001 0.01926 0.01525 -0.0823 0.8122 0.0044
-8.000 -0.4760 0.01794 0.01370 -0.0824 0.8062 0.0045
-7.750 -0.4511 0.01681 0.01238 -0.0825 0.7998 0.0047
-7.500 -0.4258 0.01577 0.01114 -0.0825 0.7939 0.0048
-7.250 -0.3997 0.01487 0.01006 -0.0825 0.7877 0.0050
-7.000 -0.3734 0.01410 0.00912 -0.0825 0.7815 0.0051
-6.750 -0.3466 0.01340 0.00828 -0.0825 0.7757 0.0053
-6.500 -0.3196 0.01280 0.00755 -0.0824 0.7695 0.0054
-6.250 -0.2924 0.01228 0.00690 -0.0824 0.7637 0.0056
-6.000 -0.2649 0.01181 0.00633 -0.0824 0.7577 0.0057
-5.750 -0.2373 0.01142 0.00584 -0.0824 0.7515 0.0058
-5.500 -0.2098 0.01083 0.00515 -0.0824 0.7457 0.0060
-5.250 -0.1823 0.01029 0.00451 -0.0824 0.7393 0.0062
-5.000 -0.1544 0.00991 0.00404 -0.0825 0.7334 0.0064
-4.750 -0.1263 0.00959 0.00367 -0.0825 0.7271 0.0067
-4.500 -0.0982 0.00934 0.00335 -0.0825 0.7208 0.0070
-4.250 -0.0699 0.00910 0.00307 -0.0825 0.7147 0.0075
-4.000 -0.0417 0.00888 0.00278 -0.0826 0.7080 0.0080
-3.750 -0.0133 0.00868 0.00252 -0.0826 0.7020 0.0083
-3.500 0.0150 0.00844 0.00223 -0.0826 0.6951 0.0089
-3.250 0.0434 0.00826 0.00199 -0.0826 0.6888 0.0098
-3.000 0.0719 0.00811 0.00180 -0.0827 0.6821 0.0108
-2.500 0.1286 0.00773 0.00145 -0.0828 0.6688 0.0302
-2.000 0.1852 0.00740 0.00123 -0.0830 0.6551 0.0706
-1.750 0.2136 0.00729 0.00115 -0.0830 0.6479 0.0893
-1.500 0.2420 0.00718 0.00108 -0.0831 0.6410 0.1119
-1.250 0.2703 0.00705 0.00103 -0.0832 0.6335 0.1454
-1.000 0.2987 0.00696 0.00098 -0.0833 0.6263 0.1720
-0.750 0.3271 0.00688 0.00095 -0.0834 0.6185 0.1980
-0.500 0.3554 0.00679 0.00093 -0.0835 0.6111 0.2322
-0.250 0.3837 0.00673 0.00092 -0.0836 0.6025 0.2644
0.000 0.4120 0.00666 0.00092 -0.0837 0.5940 0.2997
0.250 0.4401 0.00661 0.00092 -0.0837 0.5840 0.3372
0.500 0.4681 0.00656 0.00094 -0.0838 0.5720 0.3825
0.750 0.4962 0.00650 0.00097 -0.0839 0.5601 0.4309
1.000 0.5241 0.00641 0.00101 -0.0840 0.5491 0.4943
1.250 0.5517 0.00633 0.00106 -0.0840 0.5378 0.5634
1.500 0.5791 0.00624 0.00113 -0.0840 0.5257 0.6402
1.750 0.6059 0.00611 0.00121 -0.0838 0.5128 0.7311
2.000 0.6306 0.00592 0.00130 -0.0830 0.5003 0.8423
2.250 0.6611 0.00576 0.00134 -0.0833 0.4865 1.0000
2.500 0.6889 0.00590 0.00141 -0.0833 0.4727 1.0000
2.750 0.7165 0.00605 0.00149 -0.0833 0.4578 1.0000
3.000 0.7440 0.00621 0.00159 -0.0833 0.4422 1.0000
3.250 0.7714 0.00639 0.00170 -0.0832 0.4255 1.0000
3.500 0.7985 0.00660 0.00182 -0.0832 0.4064 1.0000
3.750 0.8255 0.00681 0.00194 -0.0831 0.3872 1.0000
4.000 0.8523 0.00704 0.00210 -0.0830 0.3667 1.0000
4.250 0.8789 0.00731 0.00226 -0.0829 0.3444 1.0000
4.500 0.9051 0.00761 0.00245 -0.0827 0.3202 1.0000
4.750 0.9313 0.00790 0.00265 -0.0825 0.2968 1.0000
5.000 0.9570 0.00823 0.00287 -0.0823 0.2723 1.0000
5.250 0.9827 0.00857 0.00310 -0.0821 0.2497 1.0000
5.500 1.0078 0.00896 0.00338 -0.0818 0.2231 1.0000
5.750 1.0319 0.00946 0.00370 -0.0814 0.1910 1.0000
6.000 1.0565 0.00988 0.00400 -0.0810 0.1664 1.0000
6.250 1.0810 0.01028 0.00430 -0.0807 0.1463 1.0000
6.500 1.1059 0.01064 0.00460 -0.0804 0.1310 1.0000
6.750 1.1303 0.01104 0.00492 -0.0800 0.1147 1.0000
7.000 1.1539 0.01149 0.00528 -0.0795 0.0977 1.0000
7.250 1.1771 0.01197 0.00566 -0.0789 0.0807 1.0000
7.500 1.2003 0.01244 0.00607 -0.0784 0.0665 1.0000
7.750 1.2225 0.01297 0.00652 -0.0777 0.0521 1.0000
8.000 1.2443 0.01351 0.00698 -0.0770 0.0400 1.0000
8.250 1.2664 0.01400 0.00744 -0.0763 0.0322 1.0000
8.500 1.2880 0.01453 0.00793 -0.0755 0.0249 1.0000
8.750 1.3080 0.01514 0.00850 -0.0745 0.0160 1.0000
9.000 1.3278 0.01575 0.00908 -0.0735 0.0111 1.0000
9.250 1.3481 0.01628 0.00963 -0.0726 0.0095 1.0000
9.500 1.3679 0.01681 0.01019 -0.0715 0.0085 1.0000
9.750 1.3875 0.01730 0.01073 -0.0705 0.0081 1.0000
10.000 1.4060 0.01784 0.01131 -0.0693 0.0077 1.0000
10.250 1.4230 0.01840 0.01191 -0.0678 0.0073 1.0000
10.500 1.4363 0.01902 0.01257 -0.0658 0.0070 1.0000
10.750 1.4481 0.01970 0.01330 -0.0636 0.0067 1.0000
11.000 1.4590 0.02047 0.01414 -0.0614 0.0064 1.0000
11.250 1.4686 0.02139 0.01514 -0.0592 0.0062 1.0000
11.500 1.4799 0.02224 0.01605 -0.0575 0.0061 1.0000
11.750 1.4914 0.02312 0.01699 -0.0558 0.0060 1.0000
12.000 1.5019 0.02412 0.01806 -0.0542 0.0059 1.0000
12.250 1.5119 0.02520 0.01921 -0.0527 0.0058 1.0000
12.500 1.5211 0.02638 0.02048 -0.0512 0.0057 1.0000
12.750 1.5295 0.02767 0.02185 -0.0498 0.0055 1.0000
13.000 1.5374 0.02905 0.02330 -0.0484 0.0055 1.0000
13.250 1.5440 0.03060 0.02493 -0.0472 0.0053 1.0000
13.500 1.5496 0.03230 0.02672 -0.0460 0.0053 1.0000
13.750 1.5569 0.03390 0.02838 -0.0451 0.0051 1.0000
14.000 1.5604 0.03590 0.03048 -0.0441 0.0050 1.0000
14.250 1.5657 0.03781 0.03247 -0.0434 0.0049 1.0000
14.500 1.5682 0.04008 0.03482 -0.0427 0.0048 1.0000
14.750 1.5696 0.04252 0.03735 -0.0422 0.0047 1.0000
15.000 1.5694 0.04525 0.04020 -0.0418 0.0047 1.0000
15.250 1.5669 0.04836 0.04340 -0.0417 0.0045 1.0000
15.500 1.5642 0.05163 0.04678 -0.0418 0.0044 1.0000
15.750 1.5591 0.05537 0.05064 -0.0421 0.0044 1.0000
16.000 1.5523 0.05951 0.05490 -0.0428 0.0044 1.0000
16.250 1.5418 0.06436 0.05988 -0.0439 0.0043 1.0000
16.500 1.5323 0.06931 0.06496 -0.0453 0.0042 1.0000
16.750 1.5264 0.07388 0.06965 -0.0468 0.0042 1.0000
17.000 1.5192 0.07879 0.07468 -0.0485 0.0042 1.0000
17.250 1.5116 0.08396 0.07997 -0.0504 0.0042 1.0000
17.500 1.5031 0.08943 0.08556 -0.0527 0.0042 1.0000
17.750 1.4922 0.09545 0.09171 -0.0553 0.0041 1.0000
18.000 1.4797 0.10193 0.09831 -0.0583 0.0041 1.0000
18.250 1.4690 0.10829 0.10480 -0.0613 0.0041 1.0000
18.500 1.4567 0.11499 0.11162 -0.0646 0.0041 1.0000
18.750 1.4437 0.12202 0.11878 -0.0683 0.0041 1.0000
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Polar data table (+)
Polar graphs
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