S4083 (8%) (s4083-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.84 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4083-il-1000000-n5.txt Download as CSV file: xf-s4083-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3056 0.08964 0.08813 -0.0188 1.0000 0.0067
-8.750 -0.3044 0.08609 0.08459 -0.0192 1.0000 0.0067
-8.250 -0.3037 0.07884 0.07737 -0.0200 1.0000 0.0067
-6.750 -0.2835 0.05295 0.05153 -0.0345 0.9731 0.0061
-6.500 -0.3270 0.06393 0.06241 -0.0416 0.9830 0.0061
-6.250 -0.3084 0.05853 0.05697 -0.0486 0.9734 0.0057
-6.000 -0.2812 0.05087 0.04923 -0.0589 0.9636 0.0052
-5.750 -0.2507 0.01658 0.01313 -0.0801 0.9522 0.0044
-5.500 -0.2128 0.01489 0.01117 -0.0829 0.9428 0.0046
-5.250 -0.1542 0.01328 0.00923 -0.0901 0.9285 0.0049
-5.000 -0.0952 0.01208 0.00766 -0.0973 0.8889 0.0053
-4.750 -0.0680 0.01147 0.00664 -0.0972 0.8262 0.0055
-4.500 -0.0469 0.01109 0.00591 -0.0956 0.7692 0.0057
-4.250 -0.0247 0.01068 0.00522 -0.0943 0.7251 0.0058
-4.000 -0.0012 0.01031 0.00461 -0.0932 0.6883 0.0060
-3.750 0.0229 0.01001 0.00409 -0.0923 0.6545 0.0061
-3.500 0.0476 0.00979 0.00369 -0.0916 0.6242 0.0064
-3.250 0.0730 0.00961 0.00337 -0.0909 0.5979 0.0066
-3.000 0.0985 0.00938 0.00299 -0.0903 0.5754 0.0066
-2.750 0.1242 0.00910 0.00258 -0.0898 0.5554 0.0067
-2.500 0.1502 0.00889 0.00224 -0.0892 0.5378 0.0067
-2.250 0.1764 0.00866 0.00189 -0.0887 0.5222 0.0069
-2.000 0.2028 0.00849 0.00160 -0.0883 0.5069 0.0073
-1.750 0.2294 0.00837 0.00140 -0.0878 0.4940 0.0084
-1.500 0.2562 0.00831 0.00126 -0.0875 0.4811 0.0097
-1.250 0.2829 0.00822 0.00116 -0.0871 0.4692 0.0181
-1.000 0.3096 0.00812 0.00109 -0.0868 0.4590 0.0428
-0.750 0.3359 0.00794 0.00104 -0.0864 0.4494 0.0976
-0.500 0.3623 0.00780 0.00101 -0.0861 0.4394 0.1524
-0.250 0.3884 0.00757 0.00100 -0.0858 0.4301 0.2479
0.000 0.4144 0.00740 0.00102 -0.0855 0.4216 0.3335
0.250 0.4406 0.00725 0.00104 -0.0851 0.4134 0.4134
0.500 0.4666 0.00711 0.00107 -0.0847 0.4053 0.4954
0.750 0.4924 0.00700 0.00112 -0.0843 0.3967 0.5748
1.000 0.5183 0.00692 0.00118 -0.0838 0.3880 0.6436
1.250 0.5439 0.00688 0.00123 -0.0832 0.3788 0.6983
1.500 0.5653 0.00655 0.00129 -0.0817 0.3711 0.8370
2.000 0.6399 0.00652 0.00140 -0.0858 0.3547 1.0000
2.250 0.6664 0.00662 0.00146 -0.0854 0.3477 1.0000
2.500 0.6928 0.00673 0.00152 -0.0850 0.3400 1.0000
2.750 0.7193 0.00684 0.00159 -0.0846 0.3327 1.0000
3.250 0.7719 0.00708 0.00176 -0.0838 0.3150 1.0000
3.500 0.7981 0.00722 0.00186 -0.0834 0.3061 1.0000
3.750 0.8243 0.00736 0.00196 -0.0830 0.2967 1.0000
4.000 0.8506 0.00748 0.00208 -0.0826 0.2893 1.0000
4.250 0.8766 0.00764 0.00220 -0.0822 0.2801 1.0000
4.500 0.9023 0.00783 0.00234 -0.0818 0.2673 1.0000
4.750 0.9279 0.00802 0.00248 -0.0813 0.2550 1.0000
5.000 0.9534 0.00823 0.00266 -0.0808 0.2414 1.0000
5.250 0.9781 0.00852 0.00285 -0.0802 0.2188 1.0000
5.500 1.0022 0.00887 0.00309 -0.0796 0.1933 1.0000
5.750 1.0264 0.00921 0.00334 -0.0789 0.1736 1.0000
6.000 1.0498 0.00964 0.00365 -0.0782 0.1475 1.0000
6.250 1.0708 0.01033 0.00409 -0.0771 0.1052 1.0000
6.500 1.0929 0.01090 0.00451 -0.0761 0.0764 1.0000
6.750 1.1146 0.01150 0.00497 -0.0751 0.0505 1.0000
7.000 1.1351 0.01224 0.00554 -0.0739 0.0232 1.0000
7.500 1.1789 0.01336 0.00659 -0.0719 0.0045 1.0000
7.750 1.2023 0.01374 0.00700 -0.0711 0.0038 1.0000
8.000 1.2253 0.01414 0.00745 -0.0703 0.0035 1.0000
8.250 1.2483 0.01453 0.00789 -0.0695 0.0033 1.0000
8.500 1.2707 0.01497 0.00838 -0.0686 0.0032 1.0000
8.750 1.2927 0.01544 0.00892 -0.0677 0.0030 1.0000
9.000 1.3141 0.01594 0.00949 -0.0667 0.0029 1.0000
9.250 1.3347 0.01651 0.01013 -0.0655 0.0027 1.0000
9.500 1.3549 0.01710 0.01079 -0.0643 0.0026 1.0000
9.750 1.3742 0.01774 0.01150 -0.0630 0.0025 1.0000
10.000 1.3925 0.01844 0.01229 -0.0616 0.0024 1.0000
10.250 1.4099 0.01918 0.01311 -0.0600 0.0024 1.0000
10.500 1.4254 0.02004 0.01408 -0.0582 0.0023 1.0000
10.750 1.4400 0.02092 0.01505 -0.0563 0.0022 1.0000
11.000 1.4526 0.02187 0.01610 -0.0541 0.0021 1.0000
11.250 1.4609 0.02305 0.01739 -0.0513 0.0021 1.0000
11.500 1.4628 0.02427 0.01874 -0.0475 0.0020 1.0000
11.750 1.4609 0.02567 0.02027 -0.0433 0.0019 1.0000
12.000 1.4580 0.02720 0.02193 -0.0394 0.0019 1.0000
12.250 1.4575 0.02870 0.02354 -0.0363 0.0019 1.0000
12.500 1.4554 0.03045 0.02540 -0.0336 0.0019 1.0000
12.750 1.4529 0.03243 0.02749 -0.0315 0.0019 1.0000
13.000 1.4503 0.03470 0.02989 -0.0300 0.0019 1.0000
13.250 1.4477 0.03729 0.03259 -0.0292 0.0018 1.0000
13.500 1.4438 0.04036 0.03579 -0.0292 0.0018 1.0000
13.750 1.4347 0.04447 0.04006 -0.0299 0.0018 1.0000
14.000 1.4296 0.04839 0.04410 -0.0310 0.0018 1.0000
14.250 1.4227 0.05278 0.04862 -0.0325 0.0018 1.0000
14.500 1.4137 0.05760 0.05356 -0.0342 0.0018 1.0000
14.750 1.4072 0.06215 0.05823 -0.0360 0.0018 1.0000
15.000 1.3928 0.06796 0.06417 -0.0382 0.0018 1.0000
15.250 1.3797 0.07366 0.07000 -0.0406 0.0018 1.0000
15.500 1.3656 0.07971 0.07617 -0.0431 0.0018 1.0000
15.750 1.3535 0.08561 0.08218 -0.0457 0.0018 1.0000
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Polar data table (+)
Polar graphs
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