FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.02 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs21158-il-1000000-n5.txt Download as CSV file: xf-fxs21158-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7830 0.07273 0.07055 -0.0451 1.0000 0.0012
-14.500 -0.8349 0.05986 0.05743 -0.0539 1.0000 0.0012
-14.250 -0.8556 0.05349 0.05091 -0.0580 1.0000 0.0012
-14.000 -0.8670 0.04787 0.04513 -0.0626 0.9990 0.0012
-13.750 -0.7996 0.03864 0.03528 -0.0889 0.8859 0.0012
-13.500 -0.7883 0.03602 0.03209 -0.0926 0.7699 0.0012
-13.250 -0.7933 0.03313 0.02895 -0.0935 0.7344 0.0012
-13.000 -0.7904 0.03117 0.02680 -0.0938 0.7049 0.0012
-12.750 -0.7888 0.02914 0.02459 -0.0939 0.6814 0.0012
-12.500 -0.7847 0.02745 0.02275 -0.0938 0.6648 0.0012
-12.250 -0.7861 0.02555 0.02069 -0.0932 0.6504 0.0013
-12.000 -0.7841 0.02420 0.01921 -0.0923 0.6345 0.0013
-11.750 -0.7730 0.02309 0.01794 -0.0915 0.6193 0.0013
-11.250 -0.7416 0.02127 0.01586 -0.0903 0.5963 0.0013
-11.000 -0.7233 0.02047 0.01493 -0.0898 0.5852 0.0014
-10.750 -0.7037 0.01974 0.01407 -0.0894 0.5732 0.0014
-10.500 -0.6832 0.01904 0.01324 -0.0890 0.5612 0.0014
-10.250 -0.6616 0.01842 0.01251 -0.0886 0.5515 0.0014
-10.000 -0.6403 0.01765 0.01161 -0.0882 0.5433 0.0016
-9.750 -0.6177 0.01704 0.01088 -0.0880 0.5360 0.0016
-9.500 -0.5946 0.01641 0.01014 -0.0877 0.5297 0.0018
-9.250 -0.5707 0.01586 0.00950 -0.0875 0.5230 0.0019
-9.000 -0.5462 0.01535 0.00889 -0.0874 0.5166 0.0020
-8.750 -0.5216 0.01482 0.00828 -0.0873 0.5102 0.0022
-8.500 -0.4963 0.01439 0.00776 -0.0872 0.5044 0.0023
-8.250 -0.4705 0.01398 0.00727 -0.0871 0.4993 0.0025
-8.000 -0.4444 0.01361 0.00683 -0.0871 0.4939 0.0026
-7.750 -0.4182 0.01322 0.00636 -0.0871 0.4898 0.0031
-7.500 -0.3921 0.01277 0.00586 -0.0871 0.4862 0.0042
-7.250 -0.3652 0.01249 0.00567 -0.0873 0.4828 0.0101
-7.000 -0.3375 0.01238 0.00556 -0.0873 0.4798 0.0122
-6.750 -0.3098 0.01225 0.00539 -0.0874 0.4770 0.0133
-6.500 -0.2818 0.01213 0.00526 -0.0875 0.4751 0.0143
-6.250 -0.2537 0.01204 0.00516 -0.0877 0.4729 0.0149
-6.000 -0.2254 0.01202 0.00513 -0.0878 0.4706 0.0153
-5.750 -0.1978 0.01178 0.00484 -0.0879 0.4683 0.0159
-5.500 -0.1704 0.01143 0.00442 -0.0880 0.4657 0.0166
-5.250 -0.1428 0.01119 0.00412 -0.0882 0.4625 0.0173
-5.000 -0.1146 0.01097 0.00387 -0.0883 0.4591 0.0180
-4.750 -0.0864 0.01081 0.00369 -0.0885 0.4535 0.0190
-4.500 -0.0584 0.01067 0.00349 -0.0886 0.4485 0.0197
-4.250 -0.0300 0.01048 0.00325 -0.0888 0.4454 0.0199
-4.000 -0.0015 0.01031 0.00304 -0.0890 0.4414 0.0201
-3.750 0.0269 0.01017 0.00285 -0.0891 0.4377 0.0204
-3.500 0.0553 0.01006 0.00268 -0.0893 0.4338 0.0208
-3.250 0.0839 0.00994 0.00251 -0.0894 0.4309 0.0211
-3.000 0.1125 0.00983 0.00237 -0.0896 0.4279 0.0214
-2.750 0.1411 0.00975 0.00225 -0.0897 0.4252 0.0218
-2.500 0.1697 0.00968 0.00214 -0.0899 0.4224 0.0223
-2.250 0.1982 0.00961 0.00204 -0.0901 0.4195 0.0256
-2.000 0.2269 0.00948 0.00194 -0.0903 0.4170 0.0387
-1.750 0.2553 0.00936 0.00185 -0.0905 0.4120 0.0642
-1.500 0.2837 0.00935 0.00180 -0.0906 0.4067 0.0686
-1.250 0.3123 0.00929 0.00175 -0.0908 0.4027 0.0773
-1.000 0.3409 0.00921 0.00170 -0.0910 0.3991 0.1020
-0.750 0.3695 0.00915 0.00166 -0.0912 0.3958 0.1146
-0.500 0.3979 0.00904 0.00161 -0.0914 0.3925 0.1523
-0.250 0.4264 0.00891 0.00157 -0.0917 0.3899 0.1951
0.000 0.4547 0.00865 0.00149 -0.0920 0.3866 0.2645
0.250 0.4823 0.00816 0.00143 -0.0924 0.3819 0.4116
0.500 0.5106 0.00819 0.00149 -0.0925 0.3759 0.4362
0.750 0.5391 0.00825 0.00152 -0.0926 0.3704 0.4411
1.000 0.5671 0.00834 0.00157 -0.0927 0.3614 0.4458
1.250 0.5945 0.00851 0.00166 -0.0927 0.3465 0.4507
1.500 0.6197 0.00891 0.00185 -0.0924 0.3036 0.4538
1.750 0.6410 0.00974 0.00232 -0.0916 0.2286 0.4569
2.000 0.6649 0.01028 0.00267 -0.0911 0.1806 0.4599
2.250 0.6919 0.01048 0.00282 -0.0911 0.1708 0.4626
2.500 0.7193 0.01062 0.00294 -0.0911 0.1650 0.4648
2.750 0.7450 0.01095 0.00318 -0.0909 0.1385 0.4673
3.000 0.7714 0.01119 0.00336 -0.0907 0.1270 0.4696
3.250 0.7980 0.01139 0.00355 -0.0906 0.1186 0.4729
3.500 0.8251 0.01154 0.00370 -0.0906 0.1149 0.4759
3.750 0.8504 0.01187 0.00396 -0.0903 0.0932 0.4786
4.000 0.8772 0.01204 0.00412 -0.0903 0.0913 0.4810
4.250 0.9037 0.01223 0.00430 -0.0902 0.0888 0.4832
4.500 0.9301 0.01240 0.00450 -0.0901 0.0864 0.4877
4.750 0.9562 0.01260 0.00472 -0.0899 0.0818 0.4925
5.000 0.9796 0.01305 0.00508 -0.0894 0.0571 0.4968
5.250 1.0049 0.01330 0.00533 -0.0891 0.0512 0.4995
5.500 1.0301 0.01355 0.00561 -0.0889 0.0405 0.5023
5.750 1.0528 0.01399 0.00600 -0.0882 0.0280 0.5051
6.000 1.0773 0.01428 0.00629 -0.0879 0.0239 0.5077
6.250 1.1018 0.01454 0.00657 -0.0875 0.0219 0.5102
6.750 1.1442 0.01550 0.00752 -0.0858 0.0025 0.5168
7.000 1.1665 0.01587 0.00793 -0.0851 0.0021 0.5211
7.250 1.1884 0.01624 0.00834 -0.0844 0.0018 0.5251
7.500 1.2096 0.01662 0.00876 -0.0835 0.0017 0.5282
7.750 1.2299 0.01702 0.00921 -0.0826 0.0017 0.5314
8.000 1.2493 0.01746 0.00969 -0.0815 0.0016 0.5350
8.250 1.2673 0.01792 0.01022 -0.0802 0.0015 0.5386
8.750 1.2951 0.01894 0.01135 -0.0763 0.0014 0.5464
9.000 1.3042 0.01954 0.01202 -0.0736 0.0013 0.5513
9.250 1.3116 0.02026 0.01280 -0.0708 0.0013 0.5560
9.500 1.3168 0.02112 0.01374 -0.0681 0.0012 0.5609
9.750 1.3204 0.02220 0.01490 -0.0656 0.0012 0.5664
10.250 1.3228 0.02527 0.01814 -0.0616 0.0011 0.5779
10.500 1.3240 0.02720 0.02016 -0.0603 0.0011 0.5844
10.750 1.3244 0.02941 0.02249 -0.0594 0.0011 0.5921
11.250 1.3156 0.03520 0.02851 -0.0579 0.0009 0.6105
11.500 1.3208 0.03725 0.03064 -0.0576 0.0010 0.6232
11.750 1.3118 0.04078 0.03430 -0.0571 0.0009 0.6359
12.000 1.3031 0.04435 0.03801 -0.0567 0.0009 0.6518
12.250 1.2899 0.04844 0.04226 -0.0565 0.0008 0.6724
12.500 1.2878 0.05132 0.04532 -0.0563 0.0008 0.7167
13.000 1.2964 0.05722 0.05187 -0.0588 0.0008 1.0000
13.250 1.2961 0.06032 0.05504 -0.0590 0.0008 1.0000
13.500 1.2954 0.06350 0.05828 -0.0593 0.0008 1.0000
13.750 1.2958 0.06664 0.06148 -0.0596 0.0008 1.0000
14.000 1.2964 0.06978 0.06469 -0.0600 0.0008 1.0000
14.250 1.2970 0.07301 0.06798 -0.0605 0.0008 1.0000
14.500 1.2975 0.07627 0.07131 -0.0611 0.0008 1.0000
14.750 1.2981 0.07962 0.07474 -0.0617 0.0007 1.0000
15.000 1.2990 0.08295 0.07813 -0.0624 0.0008 1.0000
15.250 1.2989 0.08648 0.08172 -0.0631 0.0008 1.0000
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