S4110 (s4110-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 100,000 Max Cl/Cd: 57.86 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4110-il-100000-n5.txt Download as CSV file: xf-s4110-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4040 0.10221 0.09691 -0.0325 1.0000 0.0295
-9.250 -0.3982 0.09921 0.09395 -0.0321 1.0000 0.0290
-9.000 -0.3951 0.09605 0.09083 -0.0324 1.0000 0.0285
-8.750 -0.3936 0.09285 0.08768 -0.0330 1.0000 0.0281
-8.500 -0.3937 0.08959 0.08448 -0.0335 1.0000 0.0278
-8.250 -0.3968 0.08613 0.08109 -0.0342 1.0000 0.0276
-8.000 -0.4011 0.08298 0.07803 -0.0345 1.0000 0.0274
-7.750 -0.4090 0.07995 0.07510 -0.0344 1.0000 0.0272
-7.500 -0.4166 0.07667 0.07192 -0.0350 1.0000 0.0271
-7.250 -0.4220 0.07292 0.06825 -0.0366 1.0000 0.0269
-7.000 -0.4270 0.06854 0.06392 -0.0392 1.0000 0.0272
-6.750 -0.4299 0.06379 0.05918 -0.0419 1.0000 0.0272
-6.500 -0.4305 0.05829 0.05362 -0.0450 1.0000 0.0273
-6.250 -0.4277 0.05242 0.04760 -0.0479 1.0000 0.0272
-6.000 -0.4206 0.04613 0.04101 -0.0508 1.0000 0.0275
-5.750 -0.3981 0.03889 0.03317 -0.0559 0.9973 0.0276
-5.500 -0.3652 0.03259 0.02604 -0.0608 0.9930 0.0279
-5.250 -0.3322 0.02825 0.02089 -0.0637 0.9887 0.0286
-5.000 -0.2978 0.02528 0.01721 -0.0658 0.9851 0.0296
-4.750 -0.2654 0.02350 0.01525 -0.0675 0.9809 0.0313
-4.500 -0.2328 0.02234 0.01388 -0.0689 0.9758 0.0344
-4.250 -0.1978 0.02106 0.01229 -0.0704 0.9719 0.0396
-4.000 -0.1657 0.02008 0.01124 -0.0716 0.9667 0.0452
-3.750 -0.1329 0.01915 0.01021 -0.0727 0.9614 0.0546
-3.500 -0.0967 0.01862 0.00961 -0.0746 0.9573 0.0701
-3.250 -0.0661 0.01813 0.00907 -0.0753 0.9506 0.0854
-3.000 -0.0316 0.01759 0.00847 -0.0768 0.9456 0.1000
-2.750 0.0030 0.01705 0.00791 -0.0782 0.9407 0.1139
-2.500 0.0343 0.01663 0.00748 -0.0790 0.9339 0.1322
-2.250 0.0711 0.01611 0.00706 -0.0808 0.9296 0.1577
-2.000 0.1015 0.01566 0.00677 -0.0815 0.9224 0.2007
-1.750 0.1358 0.01511 0.00653 -0.0829 0.9169 0.2833
-1.500 0.1671 0.01454 0.00642 -0.0837 0.9108 0.4143
-1.250 0.1964 0.01400 0.00636 -0.0838 0.9036 0.5638
-1.000 0.2239 0.01348 0.00632 -0.0829 0.8975 0.7167
-0.750 0.2561 0.01299 0.00619 -0.0824 0.8903 0.9191
-0.500 0.2994 0.01285 0.00588 -0.0852 0.8847 1.0000
-0.250 0.3280 0.01288 0.00577 -0.0852 0.8744 1.0000
0.000 0.3590 0.01289 0.00565 -0.0856 0.8652 1.0000
0.250 0.3921 0.01285 0.00549 -0.0863 0.8566 1.0000
0.500 0.4204 0.01287 0.00543 -0.0861 0.8450 1.0000
0.750 0.4495 0.01288 0.00536 -0.0861 0.8336 1.0000
1.000 0.4791 0.01288 0.00529 -0.0860 0.8220 1.0000
1.250 0.5085 0.01288 0.00522 -0.0859 0.8098 1.0000
1.500 0.5370 0.01289 0.00517 -0.0856 0.7963 1.0000
1.750 0.5646 0.01291 0.00516 -0.0851 0.7814 1.0000
2.000 0.5916 0.01296 0.00516 -0.0846 0.7651 1.0000
2.250 0.6185 0.01301 0.00518 -0.0840 0.7479 1.0000
2.500 0.6454 0.01307 0.00522 -0.0834 0.7297 1.0000
2.750 0.6725 0.01313 0.00523 -0.0827 0.7102 1.0000
3.000 0.6982 0.01323 0.00530 -0.0819 0.6877 1.0000
3.250 0.7241 0.01335 0.00536 -0.0811 0.6637 1.0000
3.500 0.7496 0.01350 0.00546 -0.0803 0.6370 1.0000
3.750 0.7745 0.01370 0.00558 -0.0793 0.6070 1.0000
4.000 0.7989 0.01394 0.00572 -0.0783 0.5736 1.0000
4.250 0.8228 0.01425 0.00589 -0.0773 0.5377 1.0000
4.500 0.8459 0.01462 0.00615 -0.0762 0.4988 1.0000
4.750 0.8685 0.01505 0.00644 -0.0750 0.4592 1.0000
5.000 0.8904 0.01557 0.00678 -0.0738 0.4184 1.0000
5.250 0.9119 0.01614 0.00718 -0.0727 0.3791 1.0000
5.500 0.9330 0.01675 0.00764 -0.0716 0.3409 1.0000
5.750 0.9539 0.01741 0.00819 -0.0704 0.3064 1.0000
6.000 0.9748 0.01809 0.00875 -0.0694 0.2745 1.0000
6.250 0.9955 0.01879 0.00935 -0.0683 0.2461 1.0000
6.500 1.0162 0.01952 0.01000 -0.0672 0.2212 1.0000
6.750 1.0369 0.02025 0.01071 -0.0662 0.1989 1.0000
7.000 1.0571 0.02102 0.01144 -0.0651 0.1798 1.0000
7.250 1.0768 0.02183 0.01219 -0.0640 0.1631 1.0000
7.500 1.0968 0.02262 0.01300 -0.0630 0.1481 1.0000
7.750 1.1161 0.02346 0.01384 -0.0618 0.1346 1.0000
8.000 1.1350 0.02434 0.01478 -0.0606 0.1227 1.0000
8.250 1.1540 0.02521 0.01572 -0.0595 0.1113 1.0000
8.500 1.1723 0.02615 0.01674 -0.0582 0.1012 1.0000
8.750 1.1890 0.02721 0.01783 -0.0568 0.0928 1.0000
9.000 1.2055 0.02823 0.01893 -0.0554 0.0843 1.0000
9.250 1.2218 0.02935 0.02017 -0.0540 0.0768 1.0000
9.500 1.2354 0.03058 0.02145 -0.0523 0.0708 1.0000
9.750 1.2506 0.03178 0.02284 -0.0508 0.0646 1.0000
10.000 1.2621 0.03304 0.02415 -0.0489 0.0597 1.0000
10.250 1.2736 0.03452 0.02578 -0.0470 0.0555 1.0000
10.500 1.2838 0.03587 0.02729 -0.0450 0.0512 1.0000
10.750 1.2900 0.03743 0.02887 -0.0429 0.0479 1.0000
11.000 1.2991 0.03919 0.03088 -0.0410 0.0448 1.0000
11.250 1.3059 0.04093 0.03285 -0.0391 0.0418 1.0000
11.500 1.3098 0.04267 0.03469 -0.0372 0.0393 1.0000
11.750 1.3114 0.04494 0.03700 -0.0355 0.0373 1.0000
12.000 1.3150 0.04737 0.03977 -0.0339 0.0356 1.0000
12.250 1.3157 0.04997 0.04265 -0.0325 0.0338 1.0000
12.500 1.3143 0.05265 0.04553 -0.0314 0.0321 1.0000
12.750 1.3117 0.05542 0.04845 -0.0306 0.0308 1.0000
13.000 1.3077 0.05846 0.05160 -0.0303 0.0297 1.0000
13.250 1.3015 0.06217 0.05538 -0.0301 0.0287 1.0000
13.500 1.2921 0.06652 0.06006 -0.0306 0.0281 1.0000
13.750 1.2803 0.07148 0.06532 -0.0316 0.0277 1.0000
14.000 1.2657 0.07711 0.07123 -0.0335 0.0273 1.0000
14.250 1.2490 0.08344 0.07782 -0.0362 0.0271 1.0000
14.500 1.2296 0.09067 0.08531 -0.0399 0.0269 1.0000
14.750 1.2080 0.09893 0.09379 -0.0447 0.0270 1.0000
15.000 1.1837 0.10852 0.10360 -0.0508 0.0272 1.0000
15.250 1.1562 0.11975 0.11501 -0.0581 0.0275 1.0000
15.500 1.1256 0.13281 0.12821 -0.0667 0.0280 1.0000
15.750 1.0921 0.14780 0.14328 -0.0760 0.0285 1.0000
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