S4110 (s4110-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 500,000 Max Cl/Cd: 107.22 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4110-il-500000.txt Download as CSV file: xf-s4110-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4055 0.08959 0.08730 -0.0346 1.0000 0.0228
-8.750 -0.4050 0.08654 0.08428 -0.0347 1.0000 0.0230
-8.500 -0.4017 0.08449 0.08225 -0.0341 1.0000 0.0234
-8.250 -0.4024 0.08192 0.07972 -0.0338 1.0000 0.0237
-8.000 -0.4028 0.08006 0.07789 -0.0328 1.0000 0.0242
-7.750 -0.4124 0.07790 0.07578 -0.0313 1.0000 0.0245
-7.500 -0.4289 0.07617 0.07413 -0.0286 1.0000 0.0246
-7.250 -0.4410 0.07386 0.07187 -0.0277 0.9999 0.0248
-7.000 -0.4137 0.06767 0.06566 -0.0386 0.9960 0.0260
-6.750 -0.3699 0.05522 0.05301 -0.0606 0.9899 0.0294
-6.500 -0.3474 0.03987 0.03712 -0.0766 0.9842 0.0305
-6.250 -0.3321 0.01978 0.01517 -0.0837 0.9762 0.0164
-6.000 -0.2988 0.01726 0.01223 -0.0856 0.9737 0.0164
-5.750 -0.2631 0.01584 0.01054 -0.0874 0.9720 0.0168
-5.500 -0.2280 0.01377 0.00818 -0.0894 0.9706 0.0173
-5.250 -0.1996 0.01268 0.00697 -0.0896 0.9651 0.0181
-5.000 -0.1651 0.01196 0.00620 -0.0911 0.9621 0.0190
-4.750 -0.1300 0.01134 0.00552 -0.0926 0.9595 0.0203
-4.500 -0.0944 0.01090 0.00500 -0.0941 0.9571 0.0221
-4.250 -0.0665 0.01018 0.00424 -0.0941 0.9505 0.0249
-4.000 -0.0344 0.00966 0.00370 -0.0948 0.9459 0.0321
-3.750 -0.0025 0.00933 0.00342 -0.0954 0.9415 0.0506
-3.500 0.0254 0.00911 0.00321 -0.0953 0.9340 0.0606
-3.250 0.0561 0.00885 0.00296 -0.0957 0.9287 0.0698
-3.000 0.0831 0.00868 0.00278 -0.0954 0.9201 0.0799
-2.750 0.1122 0.00847 0.00256 -0.0954 0.9136 0.0919
-2.500 0.1389 0.00824 0.00238 -0.0951 0.9043 0.1094
-2.250 0.1666 0.00800 0.00220 -0.0949 0.8963 0.1362
-2.000 0.1937 0.00772 0.00205 -0.0946 0.8874 0.1809
-1.750 0.2204 0.00740 0.00194 -0.0944 0.8781 0.2529
-1.500 0.2473 0.00706 0.00186 -0.0942 0.8692 0.3493
-1.250 0.2735 0.00675 0.00182 -0.0938 0.8588 0.4467
-1.000 0.2998 0.00648 0.00180 -0.0934 0.8486 0.5436
-0.750 0.3255 0.00620 0.00179 -0.0928 0.8390 0.6457
-0.500 0.3499 0.00594 0.00180 -0.0918 0.8283 0.7459
-0.250 0.3715 0.00568 0.00182 -0.0899 0.8166 0.8486
0.000 0.3992 0.00549 0.00176 -0.0891 0.8053 0.9566
0.250 0.4357 0.00549 0.00168 -0.0908 0.7937 1.0000
0.500 0.4625 0.00556 0.00165 -0.0904 0.7813 1.0000
0.750 0.4893 0.00563 0.00163 -0.0900 0.7680 1.0000
1.000 0.5161 0.00570 0.00163 -0.0896 0.7537 1.0000
1.250 0.5428 0.00578 0.00163 -0.0892 0.7385 1.0000
1.500 0.5695 0.00587 0.00165 -0.0888 0.7220 1.0000
1.750 0.5960 0.00597 0.00168 -0.0883 0.7039 1.0000
2.000 0.6222 0.00610 0.00171 -0.0878 0.6838 1.0000
2.250 0.6485 0.00623 0.00175 -0.0874 0.6621 1.0000
2.750 0.7003 0.00656 0.00190 -0.0863 0.6140 1.0000
3.000 0.7259 0.00677 0.00199 -0.0857 0.5862 1.0000
3.250 0.7509 0.00701 0.00210 -0.0851 0.5545 1.0000
3.500 0.7758 0.00729 0.00225 -0.0845 0.5225 1.0000
3.750 0.8004 0.00759 0.00241 -0.0838 0.4854 1.0000
4.000 0.8246 0.00795 0.00259 -0.0831 0.4463 1.0000
4.250 0.8487 0.00833 0.00281 -0.0824 0.4073 1.0000
4.500 0.8726 0.00875 0.00306 -0.0818 0.3663 1.0000
4.750 0.8965 0.00917 0.00331 -0.0811 0.3290 1.0000
5.000 0.9202 0.00963 0.00359 -0.0804 0.2924 1.0000
5.250 0.9441 0.01007 0.00389 -0.0798 0.2582 1.0000
5.500 0.9679 0.01052 0.00421 -0.0792 0.2279 1.0000
5.750 0.9917 0.01097 0.00453 -0.0786 0.2017 1.0000
6.000 1.0154 0.01143 0.00487 -0.0779 0.1780 1.0000
6.250 1.0394 0.01184 0.00522 -0.0773 0.1591 1.0000
6.500 1.0633 0.01227 0.00560 -0.0767 0.1427 1.0000
6.750 1.0870 0.01270 0.00598 -0.0761 0.1280 1.0000
7.000 1.1107 0.01313 0.00637 -0.0754 0.1159 1.0000
7.250 1.1341 0.01357 0.00678 -0.0748 0.1046 1.0000
7.500 1.1571 0.01405 0.00724 -0.0740 0.0940 1.0000
7.750 1.1799 0.01454 0.00770 -0.0733 0.0840 1.0000
8.000 1.2030 0.01498 0.00815 -0.0725 0.0751 1.0000
8.250 1.2253 0.01550 0.00866 -0.0717 0.0660 1.0000
8.500 1.2464 0.01612 0.00924 -0.0708 0.0575 1.0000
8.750 1.2683 0.01663 0.00978 -0.0699 0.0510 1.0000
9.000 1.2888 0.01727 0.01044 -0.0688 0.0455 1.0000
9.250 1.3094 0.01787 0.01106 -0.0678 0.0409 1.0000
9.500 1.3275 0.01870 0.01193 -0.0664 0.0366 1.0000
9.750 1.3481 0.01924 0.01254 -0.0653 0.0334 1.0000
10.000 1.3638 0.02021 0.01350 -0.0636 0.0295 1.0000
10.250 1.3821 0.02089 0.01430 -0.0623 0.0271 1.0000
10.500 1.3998 0.02158 0.01504 -0.0609 0.0247 1.0000
10.750 1.4095 0.02282 0.01632 -0.0584 0.0221 1.0000
11.000 1.4203 0.02378 0.01740 -0.0559 0.0207 1.0000
11.250 1.4327 0.02460 0.01831 -0.0537 0.0193 1.0000
11.500 1.4441 0.02547 0.01925 -0.0516 0.0180 1.0000
11.750 1.4503 0.02672 0.02056 -0.0490 0.0168 1.0000
12.000 1.4456 0.02888 0.02284 -0.0453 0.0157 1.0000
12.250 1.4563 0.02989 0.02397 -0.0436 0.0152 1.0000
12.500 1.4634 0.03123 0.02546 -0.0416 0.0145 1.0000
12.750 1.4685 0.03279 0.02714 -0.0397 0.0139 1.0000
13.000 1.4731 0.03444 0.02889 -0.0381 0.0133 1.0000
13.250 1.4759 0.03632 0.03087 -0.0365 0.0129 1.0000
13.500 1.4768 0.03848 0.03313 -0.0352 0.0125 1.0000
13.750 1.4724 0.04132 0.03609 -0.0339 0.0120 1.0000
14.000 1.4609 0.04516 0.04010 -0.0329 0.0116 1.0000
14.250 1.4522 0.04897 0.04408 -0.0325 0.0113 1.0000
14.500 1.4503 0.05211 0.04737 -0.0325 0.0112 1.0000
14.750 1.4485 0.05539 0.05080 -0.0330 0.0109 1.0000
15.000 1.4443 0.05917 0.05474 -0.0338 0.0107 1.0000
15.250 1.4358 0.06378 0.05951 -0.0350 0.0105 1.0000
15.500 1.4279 0.06858 0.06447 -0.0368 0.0103 1.0000
15.750 1.4172 0.07411 0.07017 -0.0391 0.0102 1.0000
16.000 1.4058 0.08006 0.07628 -0.0419 0.0100 1.0000
16.250 1.3924 0.08669 0.08308 -0.0452 0.0100 1.0000
16.500 1.3781 0.09376 0.09031 -0.0489 0.0099 1.0000
16.750 1.3629 0.10132 0.09803 -0.0531 0.0098 1.0000
17.000 1.3470 0.10930 0.10616 -0.0577 0.0098 1.0000
17.250 1.3296 0.11782 0.11484 -0.0627 0.0098 1.0000
17.500 1.3110 0.12685 0.12404 -0.0681 0.0098 1.0000
17.750 1.2923 0.13625 0.13359 -0.0739 0.0098 1.0000
18.000 1.2723 0.14623 0.14373 -0.0801 0.0099 1.0000
18.250 1.2504 0.15714 0.15480 -0.0871 0.0100 1.0000
18.500 1.2196 0.17120 0.16904 -0.0961 0.0102 1.0000
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Polar data table (+)
Polar graphs
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