S4110 (s4110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.93 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4110-il-1000000-n5.txt Download as CSV file: xf-s4110-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4110
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4470 0.11277 0.11099 -0.0227 1.0000 0.0058
-11.000 -0.4464 0.10858 0.10681 -0.0241 1.0000 0.0057
-10.000 -0.6887 0.02960 0.02713 -0.0799 0.9935 0.0057
-9.750 -0.6676 0.02587 0.02305 -0.0832 0.9897 0.0057
-9.500 -0.6419 0.02323 0.02010 -0.0856 0.9868 0.0058
-9.250 -0.6139 0.02111 0.01772 -0.0878 0.9848 0.0058
-9.000 -0.5840 0.01948 0.01587 -0.0896 0.9834 0.0059
-8.750 -0.5595 0.01822 0.01442 -0.0899 0.9785 0.0059
-8.500 -0.5323 0.01672 0.01270 -0.0909 0.9745 0.0060
-8.250 -0.5040 0.01490 0.01061 -0.0921 0.9712 0.0063
-8.000 -0.4776 0.01400 0.00957 -0.0923 0.9656 0.0065
-7.750 -0.4491 0.01321 0.00866 -0.0928 0.9603 0.0066
-7.500 -0.4199 0.01255 0.00789 -0.0934 0.9553 0.0068
-7.250 -0.3923 0.01197 0.00722 -0.0935 0.9479 0.0069
-7.000 -0.3638 0.01146 0.00663 -0.0938 0.9411 0.0072
-6.750 -0.3365 0.01099 0.00606 -0.0937 0.9325 0.0074
-6.500 -0.3091 0.01056 0.00554 -0.0937 0.9241 0.0077
-6.250 -0.2820 0.01017 0.00505 -0.0935 0.9150 0.0079
-6.000 -0.2550 0.00982 0.00462 -0.0933 0.9058 0.0082
-5.750 -0.2280 0.00952 0.00424 -0.0931 0.8970 0.0085
-5.500 -0.2009 0.00924 0.00387 -0.0929 0.8876 0.0086
-5.250 -0.1737 0.00899 0.00355 -0.0927 0.8788 0.0088
-5.000 -0.1466 0.00871 0.00318 -0.0924 0.8700 0.0091
-4.750 -0.1193 0.00841 0.00282 -0.0922 0.8611 0.0097
-4.500 -0.0919 0.00820 0.00254 -0.0920 0.8529 0.0103
-4.250 -0.0645 0.00801 0.00231 -0.0919 0.8440 0.0113
-4.000 -0.0369 0.00785 0.00209 -0.0917 0.8356 0.0123
-3.750 -0.0094 0.00766 0.00188 -0.0915 0.8268 0.0155
-3.500 0.0181 0.00744 0.00169 -0.0914 0.8176 0.0262
-3.250 0.0456 0.00730 0.00156 -0.0912 0.8085 0.0355
-3.000 0.0732 0.00721 0.00144 -0.0911 0.7987 0.0413
-2.750 0.1010 0.00711 0.00134 -0.0910 0.7888 0.0483
-2.500 0.1286 0.00703 0.00124 -0.0908 0.7786 0.0559
-2.250 0.1561 0.00695 0.00115 -0.0906 0.7671 0.0658
-1.750 0.2112 0.00680 0.00100 -0.0903 0.7419 0.0937
-1.500 0.2388 0.00673 0.00094 -0.0902 0.7292 0.1087
-1.250 0.2663 0.00668 0.00089 -0.0900 0.7153 0.1278
-1.000 0.2936 0.00661 0.00085 -0.0898 0.6991 0.1559
-0.750 0.3207 0.00657 0.00082 -0.0896 0.6819 0.1869
-0.500 0.3480 0.00651 0.00080 -0.0895 0.6650 0.2224
-0.250 0.3751 0.00642 0.00080 -0.0893 0.6467 0.2747
0.000 0.4021 0.00635 0.00081 -0.0892 0.6267 0.3340
0.250 0.4288 0.00628 0.00083 -0.0890 0.6044 0.3986
0.500 0.4555 0.00628 0.00087 -0.0888 0.5805 0.4521
0.750 0.4820 0.00623 0.00093 -0.0885 0.5548 0.5247
1.000 0.5083 0.00624 0.00101 -0.0882 0.5270 0.5917
1.250 0.5342 0.00626 0.00110 -0.0879 0.4960 0.6607
1.500 0.5594 0.00629 0.00121 -0.0873 0.4629 0.7401
1.750 0.5827 0.00626 0.00134 -0.0863 0.4301 0.8392
2.000 0.6035 0.00621 0.00143 -0.0844 0.4012 0.9532
2.250 0.6356 0.00641 0.00151 -0.0854 0.3728 1.0000
2.500 0.6616 0.00667 0.00163 -0.0851 0.3419 1.0000
2.750 0.6878 0.00692 0.00175 -0.0847 0.3152 1.0000
3.000 0.7141 0.00716 0.00188 -0.0844 0.2915 1.0000
3.250 0.7401 0.00743 0.00202 -0.0841 0.2643 1.0000
3.500 0.7662 0.00768 0.00217 -0.0838 0.2428 1.0000
3.750 0.7924 0.00793 0.00233 -0.0835 0.2223 1.0000
4.000 0.8183 0.00820 0.00250 -0.0831 0.2010 1.0000
4.250 0.8444 0.00845 0.00267 -0.0828 0.1842 1.0000
4.500 0.8701 0.00873 0.00286 -0.0825 0.1657 1.0000
4.750 0.8957 0.00902 0.00306 -0.0821 0.1481 1.0000
5.000 0.9215 0.00929 0.00327 -0.0817 0.1337 1.0000
5.250 0.9471 0.00957 0.00348 -0.0814 0.1209 1.0000
5.750 0.9986 0.01009 0.00393 -0.0807 0.1014 1.0000
6.000 1.0240 0.01037 0.00417 -0.0803 0.0922 1.0000
6.250 1.0492 0.01067 0.00443 -0.0798 0.0834 1.0000
6.500 1.0747 0.01094 0.00469 -0.0794 0.0765 1.0000
6.750 1.0995 0.01126 0.00497 -0.0790 0.0685 1.0000
7.000 1.1244 0.01157 0.00526 -0.0785 0.0618 1.0000
7.250 1.1492 0.01188 0.00556 -0.0780 0.0558 1.0000
7.500 1.1730 0.01229 0.00592 -0.0774 0.0472 1.0000
7.750 1.1969 0.01268 0.00628 -0.0768 0.0405 1.0000
8.000 1.2209 0.01305 0.00664 -0.0763 0.0356 1.0000
8.250 1.2446 0.01343 0.00702 -0.0756 0.0319 1.0000
8.500 1.2680 0.01383 0.00742 -0.0750 0.0284 1.0000
8.750 1.2915 0.01421 0.00782 -0.0743 0.0258 1.0000
9.000 1.3140 0.01468 0.00828 -0.0736 0.0224 1.0000
9.250 1.3369 0.01508 0.00871 -0.0729 0.0205 1.0000
9.500 1.3594 0.01552 0.00916 -0.0721 0.0186 1.0000
9.750 1.3809 0.01603 0.00968 -0.0712 0.0162 1.0000
10.000 1.4027 0.01648 0.01018 -0.0703 0.0149 1.0000
10.250 1.4238 0.01699 0.01071 -0.0694 0.0134 1.0000
10.500 1.4438 0.01757 0.01130 -0.0683 0.0117 1.0000
10.750 1.4641 0.01809 0.01187 -0.0672 0.0107 1.0000
11.000 1.4834 0.01866 0.01248 -0.0661 0.0096 1.0000
11.250 1.5015 0.01931 0.01315 -0.0647 0.0086 1.0000
11.500 1.5191 0.01995 0.01385 -0.0633 0.0079 1.0000
11.750 1.5363 0.02056 0.01453 -0.0619 0.0074 1.0000
12.000 1.5509 0.02120 0.01522 -0.0600 0.0069 1.0000
12.250 1.5631 0.02191 0.01598 -0.0577 0.0064 1.0000
12.500 1.5741 0.02270 0.01683 -0.0553 0.0060 1.0000
12.750 1.5837 0.02360 0.01780 -0.0529 0.0056 1.0000
13.000 1.5947 0.02441 0.01868 -0.0508 0.0055 1.0000
13.250 1.6047 0.02531 0.01967 -0.0487 0.0053 1.0000
13.500 1.6138 0.02629 0.02074 -0.0466 0.0052 1.0000
13.750 1.6220 0.02738 0.02193 -0.0446 0.0050 1.0000
14.000 1.6291 0.02860 0.02324 -0.0426 0.0048 1.0000
14.250 1.6354 0.02993 0.02465 -0.0408 0.0046 1.0000
14.500 1.6402 0.03144 0.02625 -0.0390 0.0045 1.0000
14.750 1.6442 0.03309 0.02799 -0.0374 0.0043 1.0000
15.000 1.6465 0.03498 0.02998 -0.0360 0.0042 1.0000
15.250 1.6476 0.03708 0.03218 -0.0347 0.0041 1.0000
15.500 1.6467 0.03949 0.03470 -0.0337 0.0039 1.0000
15.750 1.6434 0.04230 0.03764 -0.0329 0.0038 1.0000
16.000 1.6372 0.04562 0.04109 -0.0325 0.0037 1.0000
16.250 1.6330 0.04890 0.04449 -0.0325 0.0036 1.0000
16.500 1.6287 0.05239 0.04810 -0.0329 0.0036 1.0000
16.750 1.6219 0.05643 0.05227 -0.0337 0.0036 1.0000
17.000 1.6138 0.06090 0.05688 -0.0350 0.0035 1.0000
17.250 1.6025 0.06617 0.06229 -0.0369 0.0035 1.0000
17.500 1.5869 0.07249 0.06878 -0.0397 0.0035 1.0000
17.750 1.5702 0.07940 0.07585 -0.0430 0.0035 1.0000
18.000 1.5503 0.08730 0.08390 -0.0471 0.0035 1.0000
18.250 1.5240 0.09687 0.09364 -0.0524 0.0035 1.0000
18.500 1.4949 0.10737 0.10433 -0.0584 0.0035 1.0000
18.750 1.4599 0.11956 0.11670 -0.0655 0.0035 1.0000
19.000 1.4224 0.13265 0.12998 -0.0733 0.0036 1.0000
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