S4158 (s4158-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 200,000 Max Cl/Cd: 84.57 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4158-il-200000.txt Download as CSV file: xf-s4158-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2299 0.08859 0.08516 -0.0851 0.9598 0.0487
-9.000 -0.2278 0.08479 0.08137 -0.0903 0.9548 0.0489
-8.750 -0.2285 0.08059 0.07718 -0.0960 0.9487 0.0490
-8.500 -0.2130 0.07656 0.07316 -0.0903 0.9489 0.0507
-8.250 -0.2022 0.07403 0.07063 -0.0907 0.9461 0.0518
-8.000 -0.1971 0.07144 0.06805 -0.0919 0.9419 0.0535
-7.750 -0.1985 0.06851 0.06514 -0.0943 0.9364 0.0545
-7.500 -0.2000 0.06519 0.06179 -0.0975 0.9316 0.0559
-7.250 -0.2009 0.06126 0.05780 -0.1017 0.9262 0.0581
-7.000 -0.2124 0.05793 0.05391 -0.1068 0.9189 0.0614
-6.750 -0.2103 0.05232 0.04831 -0.1072 0.9154 0.0626
-6.500 -0.1978 0.04991 0.04596 -0.1065 0.9117 0.0639
-6.250 -0.1854 0.04788 0.04390 -0.1059 0.9082 0.0657
-6.000 -0.1722 0.04555 0.04142 -0.1056 0.9050 0.0692
-5.750 -0.1711 0.04281 0.03813 -0.1044 0.8994 0.0763
-5.500 -0.1566 0.04052 0.03590 -0.1036 0.8955 0.0782
-5.250 -0.1455 0.03183 0.02570 -0.0992 0.8913 0.0381
-5.000 -0.1263 0.02942 0.02292 -0.0980 0.8887 0.0382
-4.750 -0.1153 0.02786 0.02109 -0.0956 0.8829 0.0384
-4.500 -0.0920 0.02670 0.01968 -0.0946 0.8794 0.0377
-4.250 -0.0667 0.02460 0.01728 -0.0939 0.8770 0.0373
-3.750 -0.0257 0.02249 0.01480 -0.0911 0.8684 0.0382
-3.500 -0.0016 0.02116 0.01344 -0.0904 0.8651 0.0400
-3.250 0.0258 0.02042 0.01270 -0.0900 0.8626 0.0436
-3.000 0.0465 0.02018 0.01238 -0.0887 0.8581 0.0496
-2.750 0.0653 0.01967 0.01191 -0.0871 0.8525 0.0608
-2.500 0.0894 0.01871 0.01119 -0.0862 0.8494 0.1144
-2.250 0.1146 0.01782 0.01091 -0.0858 0.8472 0.2509
-2.000 0.1212 0.01732 0.01126 -0.0828 0.8390 0.4583
-1.750 0.1384 0.01656 0.01128 -0.0801 0.8355 0.6721
-1.500 0.1968 0.01597 0.01125 -0.0847 0.8350 0.9089
-1.250 0.2887 0.01579 0.01088 -0.0970 0.8357 0.9851
-1.000 0.3449 0.01560 0.01051 -0.1025 0.8343 1.0000
-0.750 0.3605 0.01586 0.01068 -0.1006 0.8276 1.0000
-0.500 0.3805 0.01591 0.01062 -0.0991 0.8221 1.0000
-0.250 0.4055 0.01579 0.01039 -0.0980 0.8191 1.0000
0.000 0.4212 0.01612 0.01066 -0.0962 0.8107 1.0000
0.250 0.4457 0.01602 0.01048 -0.0952 0.8066 1.0000
0.500 0.4723 0.01584 0.01021 -0.0943 0.8041 1.0000
0.750 0.4887 0.01621 0.01055 -0.0926 0.7949 1.0000
1.000 0.5152 0.01604 0.01032 -0.0918 0.7916 1.0000
1.250 0.5425 0.01582 0.01004 -0.0910 0.7892 1.0000
1.500 0.5601 0.01616 0.01037 -0.0896 0.7796 1.0000
1.750 0.5877 0.01591 0.01008 -0.0889 0.7766 1.0000
2.000 0.6089 0.01605 0.01022 -0.0877 0.7694 1.0000
2.250 0.6348 0.01588 0.01003 -0.0869 0.7644 1.0000
2.500 0.6633 0.01553 0.00966 -0.0863 0.7614 1.0000
2.750 0.6846 0.01563 0.00978 -0.0851 0.7527 1.0000
3.000 0.7129 0.01524 0.00940 -0.0845 0.7485 1.0000
3.250 0.7379 0.01502 0.00919 -0.0836 0.7413 1.0000
3.500 0.7657 0.01452 0.00869 -0.0828 0.7348 1.0000
3.750 0.7914 0.01419 0.00840 -0.0819 0.7266 1.0000
4.000 0.8198 0.01369 0.00790 -0.0812 0.7200 1.0000
4.250 0.8444 0.01348 0.00774 -0.0803 0.7101 1.0000
4.500 0.8731 0.01303 0.00730 -0.0798 0.7030 1.0000
4.750 0.8986 0.01279 0.00712 -0.0790 0.6919 1.0000
5.000 0.9238 0.01261 0.00698 -0.0782 0.6794 1.0000
5.250 0.9496 0.01242 0.00682 -0.0774 0.6658 1.0000
5.500 0.9757 0.01225 0.00665 -0.0766 0.6503 1.0000
5.750 1.0004 0.01218 0.00659 -0.0757 0.6300 1.0000
6.000 1.0243 0.01219 0.00651 -0.0746 0.6046 1.0000
6.250 1.0461 0.01237 0.00661 -0.0733 0.5756 1.0000
6.500 1.0663 0.01267 0.00682 -0.0718 0.5442 1.0000
6.750 1.0849 0.01307 0.00713 -0.0702 0.5104 1.0000
7.000 1.1015 0.01358 0.00749 -0.0683 0.4758 1.0000
7.250 1.1161 0.01417 0.00795 -0.0661 0.4389 1.0000
7.500 1.1282 0.01486 0.00847 -0.0636 0.4026 1.0000
7.750 1.1380 0.01561 0.00908 -0.0609 0.3643 1.0000
8.000 1.1450 0.01644 0.00976 -0.0578 0.3260 1.0000
8.250 1.1477 0.01733 0.01049 -0.0541 0.2901 1.0000
8.500 1.1502 0.01837 0.01135 -0.0506 0.2546 1.0000
8.750 1.1535 0.01955 0.01233 -0.0476 0.2198 1.0000
9.000 1.1572 0.02082 0.01342 -0.0448 0.1870 1.0000
9.250 1.1615 0.02216 0.01459 -0.0422 0.1535 1.0000
9.500 1.1646 0.02368 0.01591 -0.0396 0.1238 1.0000
9.750 1.1685 0.02522 0.01730 -0.0372 0.1032 1.0000
10.000 1.1738 0.02673 0.01877 -0.0350 0.0895 1.0000
10.250 1.1780 0.02836 0.02033 -0.0328 0.0801 1.0000
10.500 1.1868 0.02970 0.02171 -0.0310 0.0722 1.0000
10.750 1.1930 0.03132 0.02335 -0.0291 0.0660 1.0000
11.000 1.2018 0.03272 0.02481 -0.0276 0.0607 1.0000
11.250 1.2079 0.03456 0.02662 -0.0258 0.0560 1.0000
11.500 1.2186 0.03589 0.02808 -0.0244 0.0518 1.0000
11.750 1.2266 0.03753 0.02972 -0.0230 0.0480 1.0000
12.000 1.2375 0.03932 0.03161 -0.0216 0.0445 1.0000
12.250 1.2471 0.04084 0.03327 -0.0204 0.0414 1.0000
12.500 1.2571 0.04250 0.03498 -0.0192 0.0389 1.0000
12.750 1.2743 0.04483 0.03733 -0.0182 0.0359 1.0000
13.000 1.2808 0.04659 0.03932 -0.0169 0.0342 1.0000
13.250 1.2870 0.04854 0.04144 -0.0158 0.0322 1.0000
13.500 1.2927 0.05061 0.04363 -0.0147 0.0305 1.0000
13.750 1.2999 0.05277 0.04586 -0.0139 0.0292 1.0000
14.250 1.3082 0.05989 0.05348 -0.0118 0.0272 1.0000
14.500 1.3029 0.06317 0.05703 -0.0109 0.0269 1.0000
14.750 1.2945 0.06684 0.06097 -0.0103 0.0264 1.0000
15.000 1.2844 0.07078 0.06517 -0.0101 0.0259 1.0000
15.250 1.2721 0.07519 0.06984 -0.0103 0.0255 1.0000
15.500 1.2572 0.08030 0.07520 -0.0110 0.0253 1.0000
15.750 1.2429 0.08536 0.08048 -0.0123 0.0248 1.0000
16.000 1.2220 0.09206 0.08745 -0.0144 0.0250 1.0000
16.250 1.2048 0.09829 0.09389 -0.0171 0.0246 1.0000
16.500 1.1777 0.10703 0.10288 -0.0213 0.0252 1.0000
16.750 1.1547 0.11544 0.11150 -0.0260 0.0251 1.0000
17.000 1.1284 0.12527 0.12152 -0.0320 0.0256 1.0000
17.250 1.0974 0.13709 0.13352 -0.0394 0.0264 1.0000
17.500 1.0676 0.14968 0.14620 -0.0473 0.0271 1.0000
17.750 1.0395 0.16404 0.16068 -0.0564 0.0282 1.0000
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