S4158 (s4158-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 100,000 Max Cl/Cd: 55.46 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4158-il-100000-n5.txt Download as CSV file: xf-s4158-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2641 0.09879 0.09388 -0.0689 0.9506 0.0503
-9.500 -0.2512 0.09367 0.08869 -0.0700 0.9475 0.0355
-9.000 -0.2510 0.08296 0.07799 -0.0785 0.9375 0.0284
-8.750 -0.2446 0.07972 0.07475 -0.0802 0.9338 0.0279
-8.500 -0.2418 0.07605 0.07109 -0.0827 0.9293 0.0275
-8.250 -0.2420 0.07235 0.06742 -0.0853 0.9237 0.0272
-8.000 -0.2474 0.06782 0.06290 -0.0895 0.9181 0.0273
-7.750 -0.2494 0.06372 0.05876 -0.0927 0.9125 0.0268
-7.500 -0.2506 0.05894 0.05387 -0.0959 0.9073 0.0268
-7.250 -0.2507 0.05416 0.04890 -0.0981 0.9030 0.0270
-7.000 -0.2509 0.05006 0.04455 -0.0988 0.8975 0.0271
-6.750 -0.2459 0.04635 0.04056 -0.0989 0.8931 0.0271
-6.500 -0.2375 0.04270 0.03652 -0.0986 0.8897 0.0272
-6.250 -0.2295 0.03973 0.03317 -0.0975 0.8850 0.0272
-6.000 -0.2180 0.03682 0.02983 -0.0963 0.8808 0.0271
-5.750 -0.2020 0.03418 0.02671 -0.0953 0.8775 0.0272
-5.500 -0.1826 0.03182 0.02387 -0.0943 0.8750 0.0274
-5.250 -0.1671 0.03012 0.02178 -0.0926 0.8703 0.0277
-5.000 -0.1464 0.02845 0.01970 -0.0915 0.8667 0.0282
-4.750 -0.1227 0.02705 0.01799 -0.0907 0.8639 0.0288
-4.500 -0.0984 0.02570 0.01652 -0.0903 0.8616 0.0301
-4.250 -0.0788 0.02514 0.01590 -0.0892 0.8574 0.0328
-4.000 -0.0570 0.02449 0.01507 -0.0881 0.8534 0.0361
-3.750 -0.0330 0.02358 0.01405 -0.0873 0.8503 0.0386
-3.500 -0.0084 0.02283 0.01327 -0.0867 0.8478 0.0424
-3.250 0.0118 0.02238 0.01270 -0.0854 0.8435 0.0483
-2.750 0.0563 0.02137 0.01179 -0.0836 0.8357 0.0898
-2.250 0.0988 0.02028 0.01137 -0.0819 0.8277 0.2364
-2.000 0.1198 0.01967 0.01131 -0.0809 0.8233 0.3860
-1.750 0.1432 0.01901 0.01124 -0.0798 0.8204 0.5646
-1.500 0.1697 0.01842 0.01123 -0.0784 0.8183 0.7505
-1.250 0.2557 0.01808 0.01101 -0.0888 0.8187 0.9533
-1.000 0.3140 0.01807 0.01077 -0.0952 0.8168 1.0000
-0.750 0.3287 0.01837 0.01094 -0.0932 0.8096 1.0000
-0.500 0.3522 0.01841 0.01082 -0.0923 0.8057 1.0000
-0.250 0.3717 0.01860 0.01089 -0.0909 0.8002 1.0000
0.000 0.3911 0.01878 0.01096 -0.0895 0.7940 1.0000
0.250 0.4170 0.01875 0.01082 -0.0888 0.7904 1.0000
0.500 0.4337 0.01905 0.01104 -0.0871 0.7828 1.0000
0.750 0.4577 0.01908 0.01098 -0.0862 0.7778 1.0000
1.000 0.4859 0.01896 0.01078 -0.0858 0.7747 1.0000
1.250 0.5007 0.01933 0.01112 -0.0838 0.7653 1.0000
1.500 0.5283 0.01921 0.01094 -0.0834 0.7615 1.0000
1.750 0.5455 0.01951 0.01122 -0.0817 0.7528 1.0000
2.000 0.5721 0.01943 0.01111 -0.0811 0.7482 1.0000
2.250 0.5918 0.01963 0.01131 -0.0798 0.7404 1.0000
2.500 0.6171 0.01958 0.01125 -0.0791 0.7347 1.0000
2.750 0.6387 0.01969 0.01137 -0.0779 0.7273 1.0000
3.000 0.6634 0.01965 0.01135 -0.0771 0.7208 1.0000
3.250 0.6847 0.01974 0.01148 -0.0759 0.7127 1.0000
3.500 0.7111 0.01958 0.01134 -0.0753 0.7064 1.0000
3.750 0.7313 0.01969 0.01149 -0.0739 0.6967 1.0000
4.000 0.7613 0.01930 0.01116 -0.0736 0.6909 1.0000
4.250 0.7816 0.01932 0.01123 -0.0722 0.6792 1.0000
4.500 0.8043 0.01920 0.01116 -0.0709 0.6675 1.0000
4.750 0.8290 0.01899 0.01101 -0.0699 0.6555 1.0000
5.000 0.8550 0.01876 0.01085 -0.0691 0.6431 1.0000
5.250 0.8814 0.01855 0.01069 -0.0683 0.6297 1.0000
5.500 0.9074 0.01840 0.01058 -0.0675 0.6147 1.0000
5.750 0.9333 0.01829 0.01051 -0.0667 0.5980 1.0000
6.000 0.9596 0.01819 0.01046 -0.0659 0.5795 1.0000
6.250 0.9837 0.01824 0.01052 -0.0649 0.5582 1.0000
6.500 1.0078 0.01832 0.01058 -0.0639 0.5342 1.0000
6.750 1.0288 0.01855 0.01074 -0.0625 0.5050 1.0000
7.000 1.0465 0.01893 0.01105 -0.0606 0.4708 1.0000
7.250 1.0617 0.01946 0.01143 -0.0585 0.4342 1.0000
7.500 1.0742 0.02012 0.01194 -0.0562 0.3977 1.0000
7.750 1.0839 0.02087 0.01255 -0.0535 0.3623 1.0000
8.000 1.0914 0.02172 0.01326 -0.0506 0.3279 1.0000
8.250 1.0980 0.02270 0.01408 -0.0478 0.2922 1.0000
8.750 1.1114 0.02493 0.01604 -0.0428 0.2283 1.0000
9.000 1.1185 0.02616 0.01714 -0.0406 0.1995 1.0000
9.250 1.1256 0.02744 0.01831 -0.0386 0.1737 1.0000
9.500 1.1331 0.02876 0.01955 -0.0366 0.1489 1.0000
9.750 1.1404 0.03014 0.02087 -0.0348 0.1273 1.0000
10.000 1.1471 0.03161 0.02228 -0.0329 0.1096 1.0000
10.250 1.1532 0.03317 0.02381 -0.0311 0.0955 1.0000
10.500 1.1599 0.03473 0.02538 -0.0294 0.0845 1.0000
10.750 1.1659 0.03637 0.02706 -0.0278 0.0765 1.0000
11.000 1.1705 0.03816 0.02885 -0.0261 0.0700 1.0000
11.250 1.1771 0.03985 0.03065 -0.0247 0.0639 1.0000
11.500 1.1822 0.04169 0.03255 -0.0233 0.0593 1.0000
11.750 1.1865 0.04369 0.03461 -0.0218 0.0555 1.0000
12.000 1.1934 0.04550 0.03657 -0.0206 0.0513 1.0000
12.250 1.1977 0.04754 0.03871 -0.0195 0.0480 1.0000
12.500 1.2017 0.04975 0.04097 -0.0184 0.0452 1.0000
12.750 1.2091 0.05174 0.04317 -0.0174 0.0424 1.0000
13.000 1.2141 0.05392 0.04549 -0.0165 0.0398 1.0000
13.250 1.2166 0.05633 0.04796 -0.0158 0.0375 1.0000
13.500 1.2204 0.05886 0.05057 -0.0150 0.0356 1.0000
13.750 1.2257 0.06136 0.05334 -0.0143 0.0339 1.0000
14.000 1.2282 0.06414 0.05633 -0.0138 0.0320 1.0000
14.250 1.2285 0.06707 0.05942 -0.0136 0.0304 1.0000
14.500 1.2281 0.07013 0.06259 -0.0136 0.0292 1.0000
14.750 1.2273 0.07339 0.06591 -0.0137 0.0280 1.0000
15.000 1.2259 0.07709 0.06985 -0.0138 0.0272 1.0000
15.250 1.2207 0.08135 0.07441 -0.0143 0.0266 1.0000
15.500 1.2127 0.08614 0.07949 -0.0153 0.0260 1.0000
15.750 1.2028 0.09134 0.08496 -0.0167 0.0255 1.0000
16.000 1.1900 0.09718 0.09105 -0.0188 0.0251 1.0000
16.250 1.1755 0.10357 0.09770 -0.0216 0.0248 1.0000
16.500 1.1585 0.11074 0.10511 -0.0252 0.0246 1.0000
16.750 1.1394 0.11878 0.11338 -0.0296 0.0245 1.0000
17.000 1.1164 0.12827 0.12309 -0.0352 0.0249 1.0000
17.250 1.0887 0.13972 0.13472 -0.0425 0.0252 1.0000
17.500 1.0549 0.15419 0.14933 -0.0517 0.0259 1.0000
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Polar data table (+)
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