S4083 (8%) (s4083-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 200,000 Max Cl/Cd: 74.38 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4083-il-200000-n5.txt Download as CSV file: xf-s4083-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4083 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3803 0.09270 0.08930 -0.0222 1.0000 0.0217
-7.500 -0.3833 0.08931 0.08599 -0.0224 1.0000 0.0218
-7.250 -0.3867 0.08485 0.08159 -0.0225 1.0000 0.0222
-7.000 -0.3836 0.08152 0.07830 -0.0232 1.0000 0.0224
-6.750 -0.3796 0.07818 0.07497 -0.0245 1.0000 0.0226
-6.500 -0.3744 0.07487 0.07170 -0.0257 1.0000 0.0229
-6.250 -0.3676 0.07113 0.06798 -0.0281 1.0000 0.0230
-6.000 -0.3587 0.06719 0.06406 -0.0309 1.0000 0.0231
-5.750 -0.3468 0.06244 0.05928 -0.0350 1.0000 0.0230
-5.250 -0.3111 0.05040 0.04702 -0.0436 0.9991 0.0144
-5.000 -0.2723 0.04367 0.04006 -0.0520 0.9945 0.0138
-4.750 -0.2340 0.03704 0.03306 -0.0586 0.9889 0.0133
-4.500 -0.1967 0.03075 0.02626 -0.0635 0.9828 0.0132
-4.250 -0.1596 0.02599 0.02084 -0.0665 0.9763 0.0145
-4.000 -0.1263 0.02278 0.01707 -0.0682 0.9682 0.0147
-3.750 -0.0920 0.02010 0.01390 -0.0698 0.9605 0.0146
-3.500 -0.0594 0.01808 0.01146 -0.0707 0.9506 0.0146
-3.250 -0.0270 0.01646 0.00952 -0.0713 0.9390 0.0147
-3.000 0.0075 0.01511 0.00794 -0.0724 0.9265 0.0148
-2.750 0.0451 0.01387 0.00654 -0.0741 0.9119 0.0152
-2.500 0.0890 0.01274 0.00527 -0.0774 0.8941 0.0164
-2.250 0.1371 0.01199 0.00438 -0.0814 0.8674 0.0186
-2.000 0.1857 0.01141 0.00362 -0.0855 0.8288 0.0262
-1.750 0.2240 0.01091 0.00299 -0.0874 0.7840 0.0579
-1.500 0.2524 0.01041 0.00276 -0.0876 0.7407 0.1782
-1.250 0.2772 0.01006 0.00266 -0.0870 0.7032 0.3137
-1.000 0.3006 0.00981 0.00261 -0.0861 0.6711 0.4421
-0.750 0.3224 0.00953 0.00261 -0.0846 0.6433 0.5859
-0.500 0.3439 0.00928 0.00258 -0.0829 0.6198 0.7128
0.000 0.4164 0.00908 0.00239 -0.0857 0.5752 1.0000
0.250 0.4419 0.00925 0.00236 -0.0851 0.5576 1.0000
0.500 0.4675 0.00942 0.00235 -0.0845 0.5416 1.0000
0.750 0.4932 0.00959 0.00237 -0.0839 0.5269 1.0000
1.000 0.5190 0.00976 0.00240 -0.0834 0.5131 1.0000
1.250 0.5449 0.00993 0.00244 -0.0829 0.5005 1.0000
1.500 0.5707 0.01011 0.00251 -0.0824 0.4887 1.0000
1.750 0.5966 0.01029 0.00258 -0.0819 0.4775 1.0000
2.000 0.6225 0.01047 0.00268 -0.0814 0.4667 1.0000
2.250 0.6485 0.01064 0.00279 -0.0809 0.4562 1.0000
2.500 0.6744 0.01082 0.00291 -0.0805 0.4460 1.0000
2.750 0.7001 0.01102 0.00303 -0.0800 0.4361 1.0000
3.000 0.7260 0.01121 0.00320 -0.0795 0.4257 1.0000
3.250 0.7519 0.01140 0.00336 -0.0790 0.4160 1.0000
3.500 0.7775 0.01161 0.00352 -0.0785 0.4072 1.0000
3.750 0.8033 0.01180 0.00371 -0.0781 0.3978 1.0000
4.000 0.8290 0.01201 0.00394 -0.0776 0.3887 1.0000
4.250 0.8544 0.01224 0.00414 -0.0771 0.3799 1.0000
4.500 0.8801 0.01244 0.00437 -0.0766 0.3702 1.0000
4.750 0.9054 0.01267 0.00461 -0.0761 0.3604 1.0000
5.000 0.9305 0.01291 0.00486 -0.0755 0.3506 1.0000
5.250 0.9556 0.01314 0.00515 -0.0750 0.3402 1.0000
5.500 0.9808 0.01338 0.00544 -0.0744 0.3300 1.0000
5.750 1.0056 0.01364 0.00574 -0.0738 0.3193 1.0000
6.000 1.0301 0.01391 0.00604 -0.0732 0.3072 1.0000
6.250 1.0544 0.01419 0.00639 -0.0725 0.2942 1.0000
6.500 1.0785 0.01450 0.00674 -0.0718 0.2811 1.0000
6.750 1.1023 0.01483 0.00712 -0.0711 0.2674 1.0000
7.000 1.1259 0.01518 0.00753 -0.0704 0.2522 1.0000
7.250 1.1488 0.01558 0.00796 -0.0695 0.2335 1.0000
7.500 1.1696 0.01615 0.00846 -0.0685 0.2016 1.0000
7.750 1.1881 0.01699 0.00907 -0.0672 0.1603 1.0000
8.000 1.2065 0.01788 0.00980 -0.0660 0.1252 1.0000
8.250 1.2243 0.01883 0.01062 -0.0646 0.0959 1.0000
8.500 1.2404 0.01995 0.01158 -0.0631 0.0651 1.0000
8.750 1.2556 0.02112 0.01264 -0.0614 0.0401 1.0000
9.000 1.2686 0.02248 0.01394 -0.0594 0.0215 1.0000
9.250 1.2817 0.02378 0.01529 -0.0573 0.0144 1.0000
9.500 1.2951 0.02496 0.01661 -0.0553 0.0119 1.0000
9.750 1.3084 0.02606 0.01786 -0.0533 0.0103 1.0000
10.000 1.3183 0.02738 0.01929 -0.0510 0.0091 1.0000
10.250 1.3258 0.02874 0.02082 -0.0484 0.0086 1.0000
10.500 1.3306 0.03005 0.02231 -0.0454 0.0082 1.0000
10.750 1.3333 0.03148 0.02391 -0.0423 0.0079 1.0000
11.000 1.3339 0.03309 0.02569 -0.0394 0.0078 1.0000
11.250 1.3323 0.03497 0.02777 -0.0367 0.0075 1.0000
11.500 1.3296 0.03710 0.03006 -0.0346 0.0074 1.0000
11.750 1.3254 0.03961 0.03273 -0.0330 0.0072 1.0000
12.000 1.3208 0.04246 0.03574 -0.0322 0.0071 1.0000
12.250 1.3152 0.04577 0.03921 -0.0320 0.0070 1.0000
12.500 1.3098 0.04936 0.04296 -0.0324 0.0069 1.0000
12.750 1.3045 0.05320 0.04695 -0.0332 0.0069 1.0000
13.000 1.2977 0.05745 0.05136 -0.0343 0.0067 1.0000
13.250 1.2913 0.06176 0.05582 -0.0356 0.0067 1.0000
13.500 1.2850 0.06615 0.06036 -0.0369 0.0067 1.0000
13.750 1.2776 0.07083 0.06518 -0.0385 0.0066 1.0000
14.000 1.2703 0.07557 0.07007 -0.0402 0.0065 1.0000
14.250 1.2625 0.08048 0.07512 -0.0420 0.0065 1.0000
14.500 1.2544 0.08557 0.08035 -0.0440 0.0065 1.0000
14.750 1.2465 0.09080 0.08574 -0.0461 0.0065 1.0000
15.000 1.2378 0.09632 0.09141 -0.0486 0.0064 1.0000
15.250 1.2292 0.10205 0.09729 -0.0512 0.0064 1.0000
15.500 1.2204 0.10800 0.10340 -0.0540 0.0064 1.0000
15.750 1.2111 0.11423 0.10979 -0.0572 0.0064 1.0000
16.000 1.2014 0.12078 0.11650 -0.0606 0.0064 1.0000
16.250 1.1912 0.12768 0.12356 -0.0644 0.0064 1.0000
16.500 1.1804 0.13497 0.13101 -0.0685 0.0064 1.0000
16.750 1.1685 0.14277 0.13898 -0.0731 0.0065 1.0000
17.000 1.1563 0.15098 0.14734 -0.0780 0.0065 1.0000
17.250 1.1422 0.16019 0.15671 -0.0836 0.0066 1.0000
17.500 1.1260 0.17057 0.16723 -0.0898 0.0067 1.0000
17.750 1.1052 0.18335 0.18015 -0.0974 0.0069 1.0000
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Polar data table (+)
Polar graphs
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