S4158 (s4158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.33 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4158-il-1000000-n5.txt Download as CSV file: xf-s4158-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5155 0.04256 0.04003 -0.0718 0.7901 0.0056
-8.750 -0.5557 0.02660 0.02303 -0.0731 0.7880 0.0056
-8.500 -0.5500 0.02196 0.01781 -0.0721 0.7866 0.0058
-8.250 -0.5315 0.01988 0.01544 -0.0716 0.7852 0.0058
-8.000 -0.5113 0.01809 0.01338 -0.0711 0.7838 0.0059
-7.750 -0.4881 0.01692 0.01203 -0.0707 0.7823 0.0060
-7.500 -0.4639 0.01599 0.01095 -0.0705 0.7809 0.0061
-7.250 -0.4388 0.01522 0.01006 -0.0703 0.7795 0.0063
-7.000 -0.4132 0.01456 0.00929 -0.0701 0.7781 0.0064
-6.750 -0.3874 0.01391 0.00852 -0.0699 0.7767 0.0065
-6.500 -0.3613 0.01335 0.00786 -0.0697 0.7753 0.0067
-6.250 -0.3349 0.01281 0.00724 -0.0696 0.7740 0.0069
-6.000 -0.3081 0.01232 0.00668 -0.0695 0.7727 0.0072
-5.750 -0.2812 0.01184 0.00612 -0.0695 0.7713 0.0074
-5.500 -0.2541 0.01143 0.00566 -0.0694 0.7698 0.0077
-5.250 -0.2270 0.01101 0.00518 -0.0693 0.7683 0.0079
-5.000 -0.1996 0.01066 0.00478 -0.0693 0.7667 0.0081
-4.750 -0.1722 0.01035 0.00440 -0.0693 0.7651 0.0082
-4.500 -0.1446 0.01005 0.00405 -0.0693 0.7635 0.0084
-4.250 -0.1170 0.00977 0.00373 -0.0692 0.7620 0.0085
-4.000 -0.0900 0.00935 0.00324 -0.0691 0.7603 0.0089
-3.750 -0.0622 0.00906 0.00293 -0.0692 0.7586 0.0095
-3.500 -0.0341 0.00883 0.00270 -0.0692 0.7565 0.0101
-3.250 -0.0059 0.00863 0.00248 -0.0693 0.7543 0.0108
-3.000 0.0223 0.00844 0.00227 -0.0694 0.7520 0.0114
-2.750 0.0505 0.00828 0.00208 -0.0694 0.7497 0.0121
-2.500 0.0786 0.00810 0.00188 -0.0695 0.7474 0.0142
-2.250 0.1068 0.00795 0.00174 -0.0696 0.7450 0.0183
-2.000 0.1350 0.00773 0.00161 -0.0697 0.7419 0.0347
-1.750 0.1632 0.00756 0.00150 -0.0698 0.7382 0.0508
-1.500 0.1912 0.00738 0.00139 -0.0699 0.7343 0.0741
-1.250 0.2191 0.00718 0.00130 -0.0700 0.7307 0.1083
-1.000 0.2472 0.00699 0.00123 -0.0701 0.7265 0.1479
-0.750 0.2748 0.00673 0.00116 -0.0702 0.7224 0.2114
-0.500 0.3018 0.00643 0.00110 -0.0702 0.7184 0.2987
-0.250 0.3296 0.00622 0.00107 -0.0703 0.7138 0.3616
0.000 0.3567 0.00597 0.00104 -0.0704 0.7084 0.4450
0.250 0.3837 0.00574 0.00102 -0.0703 0.7029 0.5239
0.500 0.4105 0.00551 0.00103 -0.0702 0.6961 0.6073
0.750 0.4365 0.00529 0.00103 -0.0699 0.6886 0.6927
1.000 0.4608 0.00502 0.00106 -0.0691 0.6796 0.7946
1.250 0.4846 0.00476 0.00111 -0.0680 0.6696 0.9070
1.500 0.5320 0.00477 0.00114 -0.0722 0.6570 0.9656
1.750 0.5689 0.00489 0.00117 -0.0743 0.6385 0.9798
2.000 0.6025 0.00507 0.00123 -0.0757 0.6144 0.9884
2.500 0.6711 0.00544 0.00139 -0.0789 0.5682 0.9986
2.750 0.7012 0.00564 0.00150 -0.0796 0.5460 1.0000
3.000 0.7263 0.00585 0.00161 -0.0792 0.5243 1.0000
3.250 0.7509 0.00608 0.00174 -0.0788 0.5016 1.0000
3.500 0.7756 0.00631 0.00188 -0.0783 0.4803 1.0000
3.750 0.7998 0.00657 0.00204 -0.0778 0.4569 1.0000
4.000 0.8242 0.00680 0.00220 -0.0773 0.4367 1.0000
4.250 0.8479 0.00708 0.00238 -0.0767 0.4143 1.0000
4.500 0.8705 0.00744 0.00260 -0.0759 0.3836 1.0000
4.750 0.8912 0.00791 0.00288 -0.0749 0.3432 1.0000
5.000 0.9125 0.00831 0.00313 -0.0739 0.3102 1.0000
5.250 0.9321 0.00882 0.00344 -0.0727 0.2698 1.0000
5.500 0.9522 0.00928 0.00374 -0.0716 0.2373 1.0000
5.750 0.9725 0.00970 0.00404 -0.0704 0.2111 1.0000
6.000 0.9924 0.01014 0.00435 -0.0693 0.1868 1.0000
6.250 1.0134 0.01049 0.00464 -0.0683 0.1691 1.0000
6.500 1.0332 0.01091 0.00495 -0.0671 0.1496 1.0000
6.750 1.0522 0.01134 0.00530 -0.0658 0.1300 1.0000
7.000 1.0712 0.01176 0.00564 -0.0645 0.1130 1.0000
7.250 1.0880 0.01228 0.00605 -0.0629 0.0936 1.0000
7.500 1.1050 0.01274 0.00644 -0.0613 0.0784 1.0000
7.750 1.1196 0.01319 0.00684 -0.0592 0.0673 1.0000
8.000 1.1331 0.01365 0.00728 -0.0570 0.0587 1.0000
8.250 1.1479 0.01412 0.00772 -0.0551 0.0511 1.0000
8.500 1.1631 0.01462 0.00820 -0.0534 0.0446 1.0000
8.750 1.1784 0.01515 0.00871 -0.0518 0.0387 1.0000
9.000 1.1947 0.01567 0.00922 -0.0503 0.0341 1.0000
9.250 1.2107 0.01621 0.00975 -0.0489 0.0307 1.0000
9.500 1.2267 0.01677 0.01033 -0.0475 0.0276 1.0000
9.750 1.2436 0.01728 0.01087 -0.0463 0.0258 1.0000
10.000 1.2596 0.01787 0.01147 -0.0450 0.0236 1.0000
10.250 1.2744 0.01854 0.01214 -0.0436 0.0206 1.0000
10.500 1.2906 0.01913 0.01277 -0.0424 0.0195 1.0000
10.750 1.3058 0.01979 0.01345 -0.0411 0.0178 1.0000
11.000 1.3198 0.02054 0.01421 -0.0397 0.0160 1.0000
11.250 1.3345 0.02126 0.01497 -0.0385 0.0149 1.0000
11.500 1.3490 0.02200 0.01574 -0.0372 0.0138 1.0000
11.750 1.3625 0.02281 0.01658 -0.0359 0.0126 1.0000
12.000 1.3747 0.02373 0.01752 -0.0346 0.0114 1.0000
12.250 1.3879 0.02459 0.01842 -0.0333 0.0105 1.0000
12.500 1.4003 0.02550 0.01939 -0.0321 0.0099 1.0000
12.750 1.4116 0.02653 0.02045 -0.0308 0.0088 1.0000
13.000 1.4218 0.02764 0.02160 -0.0294 0.0081 1.0000
13.250 1.4328 0.02871 0.02272 -0.0282 0.0076 1.0000
13.500 1.4428 0.02987 0.02394 -0.0270 0.0070 1.0000
13.750 1.4529 0.03104 0.02518 -0.0258 0.0068 1.0000
14.000 1.4615 0.03237 0.02657 -0.0246 0.0066 1.0000
14.250 1.4693 0.03377 0.02801 -0.0234 0.0061 1.0000
14.500 1.4760 0.03532 0.02962 -0.0223 0.0057 1.0000
14.750 1.4817 0.03702 0.03140 -0.0212 0.0054 1.0000
15.000 1.4886 0.03865 0.03311 -0.0203 0.0053 1.0000
15.250 1.4953 0.04034 0.03489 -0.0194 0.0051 1.0000
15.500 1.5000 0.04229 0.03693 -0.0186 0.0050 1.0000
15.750 1.5054 0.04423 0.03894 -0.0180 0.0048 1.0000
16.000 1.5092 0.04636 0.04117 -0.0174 0.0047 1.0000
16.250 1.5125 0.04865 0.04354 -0.0170 0.0045 1.0000
16.500 1.5134 0.05127 0.04625 -0.0166 0.0044 1.0000
16.750 1.5157 0.05382 0.04888 -0.0164 0.0042 1.0000
17.000 1.5165 0.05661 0.05176 -0.0164 0.0041 1.0000
17.250 1.5145 0.05982 0.05506 -0.0166 0.0040 1.0000
17.500 1.5115 0.06329 0.05863 -0.0169 0.0038 1.0000
17.750 1.5078 0.06698 0.06244 -0.0175 0.0038 1.0000
18.000 1.5005 0.07128 0.06686 -0.0184 0.0037 1.0000
18.250 1.4926 0.07579 0.07150 -0.0195 0.0035 1.0000
18.500 1.4858 0.08031 0.07613 -0.0208 0.0035 1.0000
18.750 1.4778 0.08515 0.08109 -0.0225 0.0035 1.0000
19.000 1.4695 0.09015 0.08621 -0.0243 0.0035 1.0000
19.250 1.4612 0.09526 0.09144 -0.0263 0.0034 1.0000
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