FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 500,000 Max Cl/Cd: 96.86 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs21158-il-500000.txt Download as CSV file: xf-fxs21158-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02/1-158 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6796 0.06995 0.06752 -0.0487 1.0000 0.0047
-13.250 -0.7176 0.05940 0.05674 -0.0560 1.0000 0.0046
-13.000 -0.7284 0.05437 0.05160 -0.0593 1.0000 0.0046
-12.750 -0.7438 0.04904 0.04610 -0.0626 1.0000 0.0046
-12.500 -0.7533 0.04481 0.04173 -0.0651 1.0000 0.0045
-12.250 -0.7775 0.03896 0.03562 -0.0681 1.0000 0.0046
-12.000 -0.7800 0.03602 0.03255 -0.0693 1.0000 0.0046
-11.750 -0.7925 0.03239 0.02872 -0.0702 1.0000 0.0047
-11.500 -0.8008 0.02965 0.02583 -0.0704 1.0000 0.0047
-11.250 -0.7975 0.02738 0.02338 -0.0708 1.0000 0.0048
-11.000 -0.7909 0.02549 0.02133 -0.0701 1.0000 0.0051
-10.750 -0.7593 0.02361 0.01928 -0.0735 0.9735 0.0055
-10.500 -0.6931 0.02152 0.01692 -0.0837 0.9357 0.0060
-10.250 -0.6348 0.01994 0.01495 -0.0917 0.8617 0.0072
-10.000 -0.6108 0.02008 0.01493 -0.0912 0.7994 0.0085
-9.750 -0.5901 0.01993 0.01456 -0.0903 0.7582 0.0099
-9.500 -0.5652 0.02032 0.01484 -0.0899 0.7248 0.0113
-9.250 -0.5390 0.02084 0.01524 -0.0897 0.6969 0.0133
-9.000 -0.5131 0.02129 0.01552 -0.0895 0.6741 0.0149
-8.750 -0.4916 0.02082 0.01488 -0.0892 0.6555 0.0165
-8.500 -0.4670 0.02108 0.01509 -0.0892 0.6376 0.0178
-8.250 -0.4417 0.02144 0.01537 -0.0892 0.6220 0.0193
-8.000 -0.4169 0.02149 0.01530 -0.0891 0.6090 0.0208
-7.750 -0.3903 0.02203 0.01572 -0.0891 0.5974 0.0222
-7.500 -0.3683 0.02066 0.01410 -0.0888 0.5880 0.0233
-7.250 -0.3456 0.01959 0.01295 -0.0887 0.5788 0.0251
-7.000 -0.3204 0.01909 0.01236 -0.0886 0.5701 0.0261
-6.750 -0.2954 0.01852 0.01166 -0.0885 0.5629 0.0270
-6.500 -0.2697 0.01791 0.01095 -0.0883 0.5564 0.0279
-6.250 -0.2443 0.01730 0.01023 -0.0881 0.5509 0.0288
-6.000 -0.2182 0.01681 0.00965 -0.0879 0.5460 0.0298
-5.750 -0.1903 0.01687 0.00960 -0.0880 0.5411 0.0314
-5.500 -0.1649 0.01616 0.00878 -0.0878 0.5369 0.0323
-5.250 -0.1403 0.01521 0.00775 -0.0875 0.5331 0.0327
-5.000 -0.1146 0.01445 0.00695 -0.0873 0.5291 0.0332
-4.750 -0.0883 0.01387 0.00630 -0.0873 0.5254 0.0338
-4.500 -0.0616 0.01341 0.00575 -0.0874 0.5221 0.0343
-4.250 -0.0343 0.01302 0.00527 -0.0875 0.5190 0.0348
-4.000 -0.0063 0.01265 0.00485 -0.0877 0.5159 0.0357
-3.750 0.0217 0.01235 0.00450 -0.0879 0.5128 0.0370
-3.500 0.0498 0.01210 0.00416 -0.0880 0.5094 0.0383
-3.250 0.0779 0.01193 0.00387 -0.0882 0.5059 0.0399
-3.000 0.1065 0.01171 0.00360 -0.0883 0.5025 0.0425
-2.750 0.1348 0.01118 0.00323 -0.0887 0.4992 0.0991
-2.500 0.1604 0.00968 0.00277 -0.0897 0.4962 0.4127
-2.250 0.1889 0.00978 0.00282 -0.0897 0.4932 0.4449
-2.000 0.2176 0.00990 0.00288 -0.0898 0.4906 0.4592
-1.750 0.2465 0.00998 0.00293 -0.0900 0.4881 0.4706
-1.500 0.2753 0.01009 0.00300 -0.0901 0.4855 0.4812
-1.250 0.3038 0.01016 0.00304 -0.0901 0.4828 0.4876
-1.000 0.3324 0.01025 0.00306 -0.0902 0.4803 0.4925
-0.750 0.3609 0.01041 0.00312 -0.0904 0.4775 0.4983
-0.500 0.3893 0.01050 0.00325 -0.0904 0.4753 0.5070
-0.250 0.4179 0.01056 0.00329 -0.0905 0.4726 0.5132
0.000 0.4462 0.01057 0.00330 -0.0906 0.4691 0.5166
0.250 0.4745 0.01062 0.00331 -0.0907 0.4660 0.5197
0.500 0.5027 0.01075 0.00336 -0.0908 0.4626 0.5226
0.750 0.5313 0.01074 0.00336 -0.0909 0.4599 0.5253
1.000 0.5598 0.01073 0.00336 -0.0911 0.4567 0.5278
1.250 0.5881 0.01074 0.00339 -0.0912 0.4541 0.5304
1.500 0.6164 0.01078 0.00342 -0.0913 0.4518 0.5328
1.750 0.6446 0.01086 0.00348 -0.0914 0.4497 0.5354
2.000 0.6729 0.01095 0.00356 -0.0916 0.4477 0.5382
2.250 0.7013 0.01098 0.00361 -0.0917 0.4456 0.5407
2.500 0.7295 0.01095 0.00363 -0.0918 0.4421 0.5433
2.750 0.7574 0.01093 0.00363 -0.0919 0.4378 0.5466
3.000 0.7851 0.01099 0.00367 -0.0919 0.4336 0.5503
3.250 0.8133 0.01101 0.00373 -0.0920 0.4301 0.5539
3.500 0.8414 0.01105 0.00381 -0.0921 0.4273 0.5569
3.750 0.8692 0.01107 0.00388 -0.0922 0.4247 0.5597
4.000 0.8969 0.01114 0.00396 -0.0923 0.4222 0.5629
4.250 0.9244 0.01124 0.00408 -0.0923 0.4196 0.5664
4.500 0.9525 0.01130 0.00420 -0.0924 0.4171 0.5702
4.750 0.9801 0.01133 0.00432 -0.0925 0.4143 0.5739
5.000 1.0077 0.01139 0.00444 -0.0926 0.4113 0.5776
5.250 1.0347 0.01147 0.00453 -0.0925 0.4071 0.5817
5.750 1.0887 0.01150 0.00467 -0.0924 0.3871 0.5893
6.000 1.1152 0.01156 0.00473 -0.0923 0.3703 0.5934
6.250 1.1400 0.01177 0.00487 -0.0920 0.3508 0.5980
6.500 1.1642 0.01205 0.00513 -0.0916 0.3304 0.6026
6.750 1.1789 0.01313 0.00584 -0.0900 0.2556 0.6075
7.000 1.1848 0.01495 0.00719 -0.0872 0.1720 0.6128
7.250 1.1947 0.01626 0.00826 -0.0850 0.1166 0.6184
7.500 1.2074 0.01724 0.00912 -0.0831 0.0849 0.6255
7.750 1.2251 0.01780 0.00971 -0.0819 0.0620 0.6337
8.000 1.2384 0.01858 0.01046 -0.0800 0.0509 0.6440
8.250 1.2539 0.01914 0.01110 -0.0784 0.0380 0.6573
8.750 1.2647 0.02072 0.01288 -0.0722 0.0247 0.7028
9.000 1.2723 0.02113 0.01365 -0.0694 0.0222 0.7948
9.250 1.2734 0.02230 0.01503 -0.0668 0.0096 1.0000
9.500 1.2727 0.02389 0.01664 -0.0645 0.0065 1.0000
9.750 1.2748 0.02560 0.01841 -0.0629 0.0059 1.0000
10.000 1.2769 0.02757 0.02046 -0.0619 0.0055 1.0000
10.250 1.2762 0.03005 0.02303 -0.0611 0.0049 1.0000
10.500 1.2772 0.03255 0.02561 -0.0607 0.0047 1.0000
10.750 1.2780 0.03514 0.02828 -0.0604 0.0046 1.0000
11.000 1.2777 0.03789 0.03112 -0.0601 0.0045 1.0000
11.250 1.2752 0.04091 0.03424 -0.0598 0.0042 1.0000
11.500 1.2754 0.04366 0.03709 -0.0596 0.0043 1.0000
11.750 1.2724 0.04679 0.04031 -0.0595 0.0041 1.0000
12.000 1.2696 0.04991 0.04352 -0.0594 0.0040 1.0000
12.250 1.2659 0.05318 0.04688 -0.0593 0.0039 1.0000
12.500 1.2641 0.05627 0.05004 -0.0594 0.0039 1.0000
12.750 1.2619 0.05955 0.05341 -0.0595 0.0038 1.0000
13.000 1.2603 0.06284 0.05679 -0.0598 0.0038 1.0000
13.250 1.2582 0.06628 0.06031 -0.0601 0.0037 1.0000
13.500 1.2584 0.06950 0.06361 -0.0605 0.0037 1.0000
13.750 1.2564 0.07307 0.06726 -0.0610 0.0037 1.0000
14.000 1.2557 0.07652 0.07079 -0.0615 0.0037 1.0000
14.250 1.2543 0.08014 0.07449 -0.0622 0.0036 1.0000
14.500 1.2549 0.08353 0.07795 -0.0628 0.0037 1.0000
14.750 1.2532 0.08728 0.08179 -0.0635 0.0036 1.0000
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