SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.46 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3002-il-1000000.txt Download as CSV file: xf-s3002-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2890 0.08672 0.08517 -0.0355 1.0000 0.0119
-9.500 -0.3839 0.09111 0.08945 -0.0342 1.0000 0.0116
-9.250 -0.3820 0.08789 0.08625 -0.0352 1.0000 0.0117
-9.000 -0.3796 0.08495 0.08334 -0.0361 1.0000 0.0118
-8.750 -0.3787 0.08186 0.08027 -0.0371 1.0000 0.0119
-8.500 -0.3790 0.07890 0.07734 -0.0378 1.0000 0.0120
-8.250 -0.3829 0.07589 0.07435 -0.0382 1.0000 0.0121
-8.000 -0.3911 0.07277 0.07129 -0.0385 0.9996 0.0122
-7.750 -0.4292 0.02028 0.01678 -0.0884 0.9655 0.0090
-7.500 -0.4035 0.01835 0.01458 -0.0891 0.9570 0.0092
-7.250 -0.3791 0.01745 0.01354 -0.0889 0.9460 0.0095
-7.000 -0.3548 0.01637 0.01228 -0.0886 0.9354 0.0098
-6.750 -0.3305 0.01520 0.01088 -0.0882 0.9254 0.0101
-6.500 -0.3056 0.01420 0.00967 -0.0877 0.9153 0.0106
-6.250 -0.2800 0.01329 0.00857 -0.0874 0.9063 0.0109
-6.000 -0.2539 0.01262 0.00773 -0.0870 0.8977 0.0112
-5.750 -0.2275 0.01190 0.00689 -0.0868 0.8893 0.0114
-5.500 -0.2020 0.01090 0.00576 -0.0865 0.8814 0.0120
-5.250 -0.1747 0.01053 0.00535 -0.0864 0.8736 0.0125
-5.000 -0.1474 0.01027 0.00503 -0.0862 0.8660 0.0133
-4.750 -0.1196 0.01000 0.00470 -0.0861 0.8583 0.0142
-4.500 -0.0927 0.00943 0.00403 -0.0860 0.8507 0.0151
-4.250 -0.0649 0.00910 0.00369 -0.0859 0.8429 0.0161
-4.000 -0.0372 0.00888 0.00341 -0.0858 0.8353 0.0173
-3.750 -0.0089 0.00871 0.00320 -0.0857 0.8275 0.0183
-3.500 0.0187 0.00826 0.00269 -0.0857 0.8196 0.0204
-3.250 0.0470 0.00811 0.00252 -0.0857 0.8115 0.0224
-3.000 0.0750 0.00783 0.00218 -0.0856 0.8036 0.0249
-2.750 0.1035 0.00765 0.00198 -0.0857 0.7955 0.0274
-2.250 0.1603 0.00731 0.00159 -0.0857 0.7792 0.0367
-2.000 0.1885 0.00700 0.00142 -0.0858 0.7709 0.0804
-1.750 0.2169 0.00667 0.00131 -0.0860 0.7617 0.1535
-1.500 0.2451 0.00633 0.00122 -0.0862 0.7526 0.2437
-1.250 0.2732 0.00587 0.00114 -0.0866 0.7427 0.3812
-1.000 0.3014 0.00538 0.00109 -0.0869 0.7324 0.5409
-0.750 0.3291 0.00514 0.00112 -0.0868 0.7217 0.6533
-0.500 0.3570 0.00514 0.00116 -0.0866 0.7100 0.7014
-0.250 0.3850 0.00518 0.00119 -0.0865 0.6971 0.7246
0.000 0.4130 0.00524 0.00123 -0.0863 0.6835 0.7436
0.250 0.4409 0.00531 0.00125 -0.0861 0.6686 0.7549
0.500 0.4689 0.00541 0.00127 -0.0860 0.6519 0.7633
1.000 0.5242 0.00560 0.00134 -0.0856 0.6155 0.7811
1.250 0.5515 0.00571 0.00140 -0.0854 0.5947 0.7912
1.500 0.5785 0.00585 0.00146 -0.0851 0.5730 0.7993
1.750 0.6058 0.00599 0.00153 -0.0849 0.5498 0.8070
2.000 0.6328 0.00615 0.00159 -0.0847 0.5256 0.8129
2.250 0.6598 0.00632 0.00167 -0.0845 0.4996 0.8177
2.500 0.6869 0.00652 0.00176 -0.0843 0.4734 0.8223
2.750 0.7138 0.00672 0.00186 -0.0841 0.4475 0.8265
3.000 0.7404 0.00691 0.00197 -0.0839 0.4228 0.8308
3.250 0.7673 0.00711 0.00209 -0.0837 0.3996 0.8354
3.500 0.7942 0.00733 0.00221 -0.0836 0.3771 0.8399
3.750 0.8207 0.00752 0.00234 -0.0833 0.3562 0.8446
4.000 0.8473 0.00772 0.00248 -0.0831 0.3360 0.8499
4.250 0.8739 0.00794 0.00263 -0.0829 0.3170 0.8553
4.500 0.9000 0.00816 0.00279 -0.0826 0.2981 0.8614
4.750 0.9264 0.00837 0.00295 -0.0824 0.2801 0.8684
5.000 0.9521 0.00857 0.00312 -0.0821 0.2622 0.8767
5.250 0.9776 0.00880 0.00330 -0.0817 0.2443 0.8872
5.500 1.0019 0.00901 0.00350 -0.0810 0.2266 0.9039
5.750 1.0256 0.00912 0.00366 -0.0801 0.2103 1.0000
6.000 1.0521 0.00943 0.00389 -0.0801 0.1947 1.0000
6.250 1.0783 0.00974 0.00413 -0.0799 0.1792 1.0000
6.500 1.1043 0.01006 0.00438 -0.0798 0.1655 1.0000
6.750 1.1299 0.01039 0.00466 -0.0795 0.1522 1.0000
7.000 1.1553 0.01073 0.00493 -0.0793 0.1393 1.0000
7.250 1.1806 0.01107 0.00522 -0.0790 0.1274 1.0000
7.500 1.2057 0.01141 0.00553 -0.0786 0.1168 1.0000
7.750 1.2305 0.01178 0.00586 -0.0783 0.1065 1.0000
8.000 1.2548 0.01218 0.00621 -0.0778 0.0961 1.0000
8.250 1.2786 0.01262 0.00659 -0.0773 0.0862 1.0000
8.500 1.3029 0.01300 0.00695 -0.0769 0.0789 1.0000
8.750 1.3265 0.01342 0.00735 -0.0763 0.0712 1.0000
9.000 1.3492 0.01392 0.00780 -0.0757 0.0635 1.0000
9.250 1.3727 0.01431 0.00822 -0.0751 0.0587 1.0000
9.500 1.3943 0.01488 0.00874 -0.0743 0.0522 1.0000
9.750 1.4175 0.01526 0.00915 -0.0737 0.0494 1.0000
10.000 1.4387 0.01581 0.00968 -0.0729 0.0453 1.0000
10.250 1.4600 0.01632 0.01023 -0.0720 0.0422 1.0000
10.500 1.4816 0.01676 0.01071 -0.0712 0.0400 1.0000
10.750 1.5014 0.01734 0.01129 -0.0702 0.0375 1.0000
11.000 1.5193 0.01805 0.01203 -0.0689 0.0348 1.0000
11.250 1.5398 0.01847 0.01251 -0.0679 0.0336 1.0000
11.500 1.5585 0.01901 0.01309 -0.0668 0.0321 1.0000
11.750 1.5747 0.01965 0.01376 -0.0652 0.0305 1.0000
12.000 1.5842 0.02052 0.01466 -0.0626 0.0284 1.0000
12.250 1.5980 0.02110 0.01530 -0.0606 0.0276 1.0000
12.500 1.6120 0.02167 0.01594 -0.0588 0.0266 1.0000
12.750 1.6248 0.02234 0.01665 -0.0570 0.0254 1.0000
13.000 1.6349 0.02320 0.01754 -0.0549 0.0239 1.0000
13.250 1.6398 0.02445 0.01884 -0.0524 0.0223 1.0000
13.500 1.6538 0.02513 0.01959 -0.0511 0.0217 1.0000
13.750 1.6646 0.02607 0.02060 -0.0495 0.0209 1.0000
14.000 1.6738 0.02717 0.02175 -0.0479 0.0199 1.0000
14.250 1.6805 0.02850 0.02313 -0.0463 0.0191 1.0000
14.500 1.6825 0.03028 0.02498 -0.0445 0.0180 1.0000
14.750 1.6888 0.03180 0.02659 -0.0432 0.0174 1.0000
15.000 1.6967 0.03324 0.02812 -0.0422 0.0169 1.0000
15.250 1.7024 0.03492 0.02988 -0.0412 0.0163 1.0000
15.500 1.7063 0.03686 0.03190 -0.0403 0.0157 1.0000
15.750 1.7081 0.03910 0.03421 -0.0395 0.0150 1.0000
16.000 1.7057 0.04189 0.03708 -0.0390 0.0144 1.0000
16.250 1.7005 0.04515 0.04045 -0.0387 0.0138 1.0000
16.500 1.7029 0.04769 0.04309 -0.0387 0.0135 1.0000
16.750 1.7021 0.05071 0.04622 -0.0389 0.0131 1.0000
17.000 1.6998 0.05408 0.04969 -0.0394 0.0127 1.0000
17.250 1.6952 0.05793 0.05364 -0.0403 0.0123 1.0000
17.500 1.6880 0.06232 0.05814 -0.0415 0.0119 1.0000
17.750 1.6779 0.06739 0.06333 -0.0433 0.0115 1.0000
18.000 1.6633 0.07342 0.06949 -0.0457 0.0112 1.0000
18.250 1.6458 0.08022 0.07642 -0.0487 0.0109 1.0000
18.500 1.6267 0.08762 0.08397 -0.0522 0.0107 1.0000
18.750 1.6117 0.09443 0.09093 -0.0556 0.0106 1.0000
19.000 1.5935 0.10203 0.09868 -0.0595 0.0105 1.0000
19.250 1.5746 0.10996 0.10675 -0.0637 0.0104 1.0000
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Polar data table (+)
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