S4083 (8%) (s4083-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.27 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4083-il-1000000.txt Download as CSV file: xf-s4083-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3896 0.08516 0.08365 -0.0150 1.0000 0.0088
-7.250 -0.3944 0.08263 0.08115 -0.0144 1.0000 0.0091
-7.000 -0.3998 0.07981 0.07837 -0.0142 1.0000 0.0093
-6.750 -0.3979 0.07620 0.07478 -0.0162 1.0000 0.0095
-6.500 -0.3899 0.07217 0.07076 -0.0200 0.9999 0.0099
-6.250 -0.3577 0.06583 0.06440 -0.0305 0.9978 0.0099
-6.000 -0.3222 0.05894 0.05744 -0.0418 0.9954 0.0100
-5.750 -0.2399 0.02929 0.02774 -0.0604 0.9871 0.0103
-5.500 -0.2154 0.02298 0.02127 -0.0671 0.9830 0.0106
-5.250 -0.1889 0.01883 0.01695 -0.0712 0.9781 0.0109
-5.000 -0.1878 0.02993 0.02766 -0.0743 0.9810 0.0110
-4.750 -0.1551 0.02649 0.02400 -0.0773 0.9768 0.0116
-4.500 -0.1234 0.02298 0.02020 -0.0793 0.9718 0.0123
-4.000 -0.0623 0.01350 0.00941 -0.0802 0.9577 0.0102
-3.750 -0.0283 0.01133 0.00691 -0.0814 0.9495 0.0103
-3.500 0.0130 0.00974 0.00511 -0.0842 0.9378 0.0106
-3.250 0.0749 0.00858 0.00377 -0.0917 0.9179 0.0109
-3.000 0.1217 0.00818 0.00312 -0.0958 0.8613 0.0118
-2.750 0.1450 0.00799 0.00260 -0.0945 0.7980 0.0118
-2.500 0.1669 0.00787 0.00220 -0.0929 0.7456 0.0120
-2.250 0.1901 0.00778 0.00188 -0.0917 0.7024 0.0124
-2.000 0.2142 0.00772 0.00162 -0.0907 0.6654 0.0136
-1.750 0.2392 0.00763 0.00135 -0.0898 0.6348 0.0171
-1.500 0.2643 0.00743 0.00118 -0.0891 0.6084 0.0551
-1.250 0.2896 0.00728 0.00111 -0.0885 0.5847 0.1105
-1.000 0.3146 0.00708 0.00107 -0.0880 0.5639 0.1981
-0.750 0.3399 0.00685 0.00106 -0.0876 0.5461 0.2999
-0.500 0.3649 0.00660 0.00107 -0.0870 0.5294 0.4230
-0.250 0.3895 0.00636 0.00111 -0.0864 0.5137 0.5503
0.000 0.4143 0.00621 0.00116 -0.0857 0.4996 0.6528
0.250 0.4377 0.00600 0.00118 -0.0846 0.4873 0.7536
0.500 0.4866 0.00562 0.00121 -0.0892 0.4722 1.0000
0.750 0.5126 0.00572 0.00123 -0.0887 0.4605 1.0000
1.000 0.5387 0.00584 0.00125 -0.0881 0.4489 1.0000
1.250 0.5650 0.00594 0.00128 -0.0877 0.4376 1.0000
1.500 0.5914 0.00603 0.00132 -0.0873 0.4277 1.0000
1.750 0.6176 0.00614 0.00136 -0.0868 0.4183 1.0000
2.000 0.6439 0.00625 0.00142 -0.0864 0.4090 1.0000
2.250 0.6704 0.00635 0.00148 -0.0860 0.4005 1.0000
2.500 0.6966 0.00647 0.00154 -0.0856 0.3920 1.0000
2.750 0.7232 0.00657 0.00161 -0.0852 0.3835 1.0000
3.000 0.7495 0.00669 0.00170 -0.0848 0.3749 1.0000
3.250 0.7757 0.00682 0.00178 -0.0844 0.3660 1.0000
3.500 0.8022 0.00693 0.00187 -0.0840 0.3576 1.0000
3.750 0.8283 0.00707 0.00197 -0.0836 0.3491 1.0000
4.000 0.8547 0.00718 0.00209 -0.0832 0.3413 1.0000
4.250 0.8809 0.00732 0.00220 -0.0828 0.3332 1.0000
4.750 0.9330 0.00761 0.00244 -0.0820 0.3124 1.0000
5.000 0.9590 0.00776 0.00259 -0.0816 0.3032 1.0000
5.250 0.9847 0.00794 0.00274 -0.0812 0.2933 1.0000
5.500 1.0103 0.00813 0.00290 -0.0807 0.2813 1.0000
5.750 1.0356 0.00835 0.00308 -0.0802 0.2659 1.0000
6.000 1.0605 0.00860 0.00328 -0.0797 0.2466 1.0000
6.250 1.0843 0.00898 0.00353 -0.0789 0.2182 1.0000
6.500 1.1079 0.00937 0.00381 -0.0782 0.1928 1.0000
6.750 1.1312 0.00979 0.00412 -0.0775 0.1703 1.0000
7.000 1.1542 0.01024 0.00446 -0.0767 0.1460 1.0000
7.250 1.1758 0.01083 0.00490 -0.0757 0.1159 1.0000
7.500 1.1967 0.01150 0.00540 -0.0746 0.0850 1.0000
7.750 1.2167 0.01224 0.00597 -0.0733 0.0567 1.0000
8.000 1.2342 0.01325 0.00675 -0.0717 0.0228 1.0000
8.250 1.2527 0.01415 0.00756 -0.0701 0.0081 1.0000
8.500 1.2746 0.01466 0.00813 -0.0691 0.0069 1.0000
8.750 1.2954 0.01528 0.00880 -0.0679 0.0059 1.0000
9.000 1.3148 0.01602 0.00966 -0.0665 0.0054 1.0000
9.250 1.3351 0.01662 0.01035 -0.0653 0.0052 1.0000
9.500 1.3541 0.01733 0.01115 -0.0638 0.0050 1.0000
9.750 1.3719 0.01811 0.01202 -0.0622 0.0048 1.0000
10.000 1.3887 0.01893 0.01295 -0.0605 0.0046 1.0000
10.250 1.4050 0.01975 0.01386 -0.0588 0.0044 1.0000
10.500 1.4196 0.02064 0.01485 -0.0568 0.0043 1.0000
10.750 1.4324 0.02161 0.01591 -0.0547 0.0041 1.0000
11.000 1.4427 0.02267 0.01708 -0.0521 0.0040 1.0000
11.250 1.4491 0.02375 0.01826 -0.0489 0.0040 1.0000
11.500 1.4517 0.02489 0.01950 -0.0452 0.0039 1.0000
11.750 1.4524 0.02617 0.02089 -0.0415 0.0039 1.0000
12.000 1.4513 0.02763 0.02246 -0.0380 0.0038 1.0000
12.250 1.4455 0.02954 0.02448 -0.0345 0.0037 1.0000
12.500 1.4418 0.03151 0.02658 -0.0319 0.0037 1.0000
12.750 1.4363 0.03390 0.02909 -0.0300 0.0037 1.0000
13.000 1.4294 0.03679 0.03211 -0.0287 0.0037 1.0000
13.250 1.4195 0.04041 0.03586 -0.0283 0.0036 1.0000
13.500 1.4134 0.04400 0.03961 -0.0285 0.0036 1.0000
13.750 1.4061 0.04803 0.04376 -0.0293 0.0036 1.0000
14.000 1.3937 0.05291 0.04879 -0.0305 0.0035 1.0000
14.250 1.3814 0.05794 0.05396 -0.0318 0.0035 1.0000
14.500 1.3753 0.06231 0.05845 -0.0334 0.0035 1.0000
14.750 1.3656 0.06727 0.06353 -0.0351 0.0035 1.0000
15.000 1.3486 0.07336 0.06978 -0.0372 0.0035 1.0000
15.250 1.3384 0.07873 0.07527 -0.0394 0.0035 1.0000
15.500 1.3221 0.08524 0.08193 -0.0421 0.0034 1.0000
15.750 1.3164 0.09034 0.08713 -0.0447 0.0035 1.0000
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Polar data table (+)
Polar graphs
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