S4158 (s4158-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 100,000 Max Cl/Cd: 57.12 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4158-il-100000.txt Download as CSV file: xf-s4158-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4158
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4471 0.10795 0.10385 -0.0284 1.0000 0.0881
-8.000 -0.4732 0.10699 0.10297 -0.0276 1.0000 0.0884
-7.750 -0.4943 0.10509 0.10113 -0.0287 1.0000 0.0885
-7.500 -0.4892 0.10049 0.09658 -0.0250 1.0000 0.0898
-7.250 -0.4689 0.09729 0.09336 -0.0202 1.0000 0.0929
-7.000 -0.4744 0.09496 0.09107 -0.0196 0.9989 0.0951
-6.750 -0.4711 0.09132 0.08743 -0.0237 0.9955 0.0985
-6.500 -0.4855 0.08632 0.08212 -0.0407 0.9892 0.1030
-6.250 -0.4676 0.08175 0.07778 -0.0358 0.9875 0.1050
-6.000 -0.4509 0.07894 0.07498 -0.0351 0.9847 0.1093
-5.750 -0.4500 0.07382 0.06951 -0.0450 0.9797 0.1181
-5.500 -0.4348 0.07098 0.06687 -0.0415 0.9769 0.1214
-5.250 -0.4184 0.06665 0.06221 -0.0480 0.9727 0.1332
-5.000 -0.4031 0.06452 0.06023 -0.0455 0.9694 0.1407
-4.750 -0.3913 0.06120 0.05678 -0.0470 0.9653 0.1513
-4.500 -0.3714 0.05797 0.05340 -0.0494 0.9612 0.1651
-4.250 -0.3492 0.05514 0.05045 -0.0511 0.9571 0.1803
-4.000 -0.3350 0.05276 0.04798 -0.0508 0.9525 0.1955
-3.750 -0.2772 0.03893 0.03182 -0.0570 0.9501 0.0718
-3.500 -0.2418 0.03545 0.02763 -0.0583 0.9463 0.0650
-3.250 -0.2143 0.03367 0.02514 -0.0576 0.9417 0.0623
-3.000 -0.1872 0.03191 0.02308 -0.0576 0.9369 0.0633
-2.750 -0.1508 0.03104 0.02209 -0.0594 0.9323 0.0697
-2.500 -0.1270 0.03019 0.02099 -0.0586 0.9267 0.0729
-2.250 -0.0965 0.02903 0.01976 -0.0589 0.9215 0.0783
-2.000 -0.0586 0.02830 0.01910 -0.0606 0.9169 0.0960
-1.750 -0.0418 0.02758 0.01850 -0.0588 0.9100 0.1305
-1.500 0.0321 0.02398 0.01835 -0.0668 0.9081 0.9998
-1.250 0.0703 0.02457 0.01846 -0.0690 0.9023 1.0000
-1.000 0.0878 0.02490 0.01852 -0.0676 0.8942 1.0000
-0.750 0.1255 0.02548 0.01880 -0.0697 0.8881 1.0000
-0.500 0.1440 0.02584 0.01897 -0.0685 0.8795 1.0000
-0.250 0.1756 0.02636 0.01926 -0.0694 0.8723 1.0000
0.000 0.2022 0.02678 0.01952 -0.0696 0.8642 1.0000
0.250 0.2268 0.02726 0.01985 -0.0693 0.8557 1.0000
0.500 0.2624 0.02769 0.02013 -0.0709 0.8486 1.0000
0.750 0.2817 0.02814 0.02047 -0.0697 0.8389 1.0000
1.000 0.3244 0.02853 0.02075 -0.0723 0.8331 1.0000
1.250 0.3394 0.02897 0.02112 -0.0705 0.8223 1.0000
1.500 0.3704 0.02938 0.02145 -0.0711 0.8148 1.0000
1.750 0.3992 0.02972 0.02173 -0.0714 0.8062 1.0000
2.000 0.4200 0.03016 0.02213 -0.0705 0.7963 1.0000
2.250 0.4606 0.03033 0.02226 -0.0724 0.7904 1.0000
2.500 0.4773 0.03078 0.02269 -0.0708 0.7793 1.0000
2.750 0.5239 0.03077 0.02268 -0.0735 0.7749 1.0000
3.000 0.5387 0.03118 0.02308 -0.0715 0.7629 1.0000
3.250 0.5597 0.03151 0.02342 -0.0705 0.7524 1.0000
3.500 0.6036 0.03127 0.02321 -0.0725 0.7472 1.0000
3.750 0.6222 0.03155 0.02354 -0.0710 0.7356 1.0000
4.000 0.6714 0.03093 0.02298 -0.0734 0.7314 1.0000
4.250 0.6937 0.03090 0.02300 -0.0722 0.7198 1.0000
4.500 0.7171 0.03080 0.02298 -0.0710 0.7082 1.0000
4.750 0.7625 0.02977 0.02205 -0.0723 0.7022 1.0000
5.000 0.7950 0.02906 0.02142 -0.0719 0.6926 1.0000
5.250 0.8217 0.02857 0.02102 -0.0709 0.6815 1.0000
5.500 0.8701 0.02673 0.01935 -0.0717 0.6778 1.0000
5.750 0.8971 0.02605 0.01878 -0.0705 0.6663 1.0000
6.000 0.9308 0.02496 0.01781 -0.0699 0.6562 1.0000
6.250 0.9792 0.02300 0.01604 -0.0707 0.6493 1.0000
6.500 1.0138 0.02187 0.01503 -0.0702 0.6352 1.0000
6.750 1.0429 0.02102 0.01428 -0.0689 0.6155 1.0000
7.000 1.0780 0.01991 0.01321 -0.0683 0.5912 1.0000
7.250 1.1004 0.01965 0.01295 -0.0664 0.5603 1.0000
7.500 1.1196 0.01969 0.01295 -0.0643 0.5255 1.0000
7.750 1.1373 0.01991 0.01305 -0.0620 0.4874 1.0000
8.000 1.1501 0.02043 0.01342 -0.0593 0.4467 1.0000
8.250 1.1580 0.02118 0.01401 -0.0560 0.4048 1.0000
8.500 1.1617 0.02210 0.01474 -0.0524 0.3626 1.0000
8.750 1.1612 0.02318 0.01562 -0.0483 0.3222 1.0000
9.000 1.1596 0.02451 0.01670 -0.0444 0.2814 1.0000
9.250 1.1572 0.02611 0.01800 -0.0408 0.2417 1.0000
9.500 1.1550 0.02794 0.01952 -0.0375 0.2044 1.0000
9.750 1.1549 0.02989 0.02116 -0.0346 0.1733 1.0000
10.000 1.1583 0.03175 0.02283 -0.0321 0.1480 1.0000
10.250 1.1662 0.03352 0.02451 -0.0301 0.1290 1.0000
10.500 1.1781 0.03521 0.02614 -0.0285 0.1146 1.0000
10.750 1.1915 0.03689 0.02776 -0.0271 0.1027 1.0000
11.000 1.2138 0.03869 0.02943 -0.0263 0.0925 1.0000
11.250 1.2276 0.04034 0.03124 -0.0250 0.0845 1.0000
11.500 1.2528 0.04252 0.03351 -0.0246 0.0771 1.0000
11.750 1.2712 0.04448 0.03552 -0.0238 0.0708 1.0000
12.000 1.2903 0.04728 0.03859 -0.0230 0.0658 1.0000
12.250 1.3027 0.04981 0.04140 -0.0217 0.0622 1.0000
12.500 1.3326 0.05403 0.04558 -0.0227 0.0571 1.0000
12.750 1.3202 0.05602 0.04796 -0.0193 0.0559 1.0000
13.000 1.3128 0.05908 0.05142 -0.0168 0.0549 1.0000
13.250 1.3030 0.06260 0.05531 -0.0146 0.0541 1.0000
13.500 1.2898 0.06639 0.05944 -0.0126 0.0535 1.0000
13.750 1.2740 0.07055 0.06392 -0.0111 0.0532 1.0000
14.000 1.2551 0.07510 0.06878 -0.0101 0.0532 1.0000
14.250 1.2335 0.08010 0.07406 -0.0098 0.0532 1.0000
14.500 1.2098 0.08561 0.07983 -0.0102 0.0535 1.0000
14.750 1.1838 0.09174 0.08620 -0.0115 0.0538 1.0000
15.000 1.1569 0.09857 0.09324 -0.0139 0.0543 1.0000
15.250 1.1289 0.10622 0.10108 -0.0174 0.0549 1.0000
15.500 1.1006 0.11489 0.10990 -0.0220 0.0556 1.0000
15.750 1.0756 0.12405 0.11916 -0.0272 0.0563 1.0000
16.000 1.0548 0.13347 0.12864 -0.0322 0.0570 1.0000
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Polar data table (+)
Polar graphs
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