SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.08 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3002-il-1000000-n5.txt Download as CSV file: xf-s3002-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4183 0.13132 0.12951 -0.0181 1.0000 0.0045
-10.250 -0.7034 0.02588 0.02302 -0.0809 0.9855 0.0047
-10.000 -0.6814 0.02275 0.01952 -0.0830 0.9787 0.0049
-9.750 -0.6550 0.02060 0.01708 -0.0848 0.9723 0.0050
-9.500 -0.6295 0.01911 0.01538 -0.0855 0.9633 0.0052
-9.250 -0.6035 0.01776 0.01381 -0.0862 0.9540 0.0053
-9.000 -0.5782 0.01667 0.01253 -0.0864 0.9426 0.0054
-8.750 -0.5538 0.01577 0.01145 -0.0862 0.9303 0.0055
-8.500 -0.5289 0.01505 0.01057 -0.0859 0.9188 0.0056
-8.250 -0.5038 0.01440 0.00977 -0.0857 0.9083 0.0057
-8.000 -0.4785 0.01381 0.00904 -0.0854 0.8980 0.0058
-7.750 -0.4535 0.01294 0.00801 -0.0852 0.8885 0.0060
-7.500 -0.4276 0.01236 0.00731 -0.0850 0.8798 0.0062
-7.250 -0.4011 0.01190 0.00677 -0.0848 0.8713 0.0064
-7.000 -0.3743 0.01152 0.00630 -0.0847 0.8637 0.0066
-6.750 -0.3472 0.01115 0.00585 -0.0846 0.8559 0.0069
-6.500 -0.3201 0.01080 0.00542 -0.0845 0.8488 0.0071
-6.250 -0.2927 0.01046 0.00501 -0.0844 0.8415 0.0074
-5.750 -0.2375 0.00988 0.00429 -0.0843 0.8276 0.0081
-5.500 -0.2099 0.00955 0.00391 -0.0843 0.8205 0.0088
-5.250 -0.1819 0.00933 0.00367 -0.0843 0.8136 0.0094
-5.000 -0.1540 0.00912 0.00340 -0.0842 0.8060 0.0101
-4.750 -0.1259 0.00891 0.00314 -0.0842 0.7986 0.0107
-4.500 -0.0979 0.00870 0.00289 -0.0842 0.7903 0.0117
-4.250 -0.0697 0.00854 0.00270 -0.0842 0.7822 0.0128
-4.000 -0.0416 0.00841 0.00251 -0.0842 0.7734 0.0139
-3.750 -0.0134 0.00824 0.00233 -0.0842 0.7644 0.0155
-3.500 0.0148 0.00814 0.00218 -0.0842 0.7546 0.0171
-3.250 0.0430 0.00801 0.00201 -0.0842 0.7438 0.0185
-3.000 0.0713 0.00787 0.00185 -0.0842 0.7334 0.0202
-2.750 0.0995 0.00778 0.00170 -0.0841 0.7231 0.0218
-2.500 0.1278 0.00768 0.00157 -0.0841 0.7121 0.0241
-2.250 0.1561 0.00759 0.00145 -0.0842 0.7010 0.0272
-2.000 0.1844 0.00750 0.00134 -0.0842 0.6893 0.0323
-1.750 0.2126 0.00737 0.00124 -0.0842 0.6765 0.0529
-1.500 0.2408 0.00723 0.00116 -0.0843 0.6630 0.0851
-1.250 0.2690 0.00712 0.00110 -0.0843 0.6483 0.1204
-1.000 0.2971 0.00700 0.00105 -0.0844 0.6324 0.1647
-0.750 0.3252 0.00679 0.00101 -0.0846 0.6156 0.2459
-0.500 0.3532 0.00657 0.00098 -0.0848 0.5973 0.3395
-0.250 0.3811 0.00635 0.00097 -0.0850 0.5771 0.4430
0.000 0.4087 0.00606 0.00100 -0.0852 0.5566 0.5850
0.250 0.4360 0.00600 0.00109 -0.0851 0.5343 0.6712
0.500 0.4635 0.00613 0.00115 -0.0850 0.5103 0.6936
0.750 0.4910 0.00627 0.00122 -0.0848 0.4865 0.7093
1.000 0.5184 0.00642 0.00130 -0.0847 0.4638 0.7273
1.250 0.5458 0.00658 0.00139 -0.0845 0.4415 0.7421
1.750 0.6005 0.00692 0.00157 -0.0842 0.3992 0.7618
2.000 0.6278 0.00709 0.00166 -0.0841 0.3787 0.7678
2.500 0.6824 0.00745 0.00186 -0.0839 0.3399 0.7765
2.750 0.7096 0.00764 0.00196 -0.0838 0.3211 0.7801
3.000 0.7368 0.00781 0.00208 -0.0836 0.3051 0.7835
3.250 0.7639 0.00799 0.00220 -0.0835 0.2891 0.7871
3.500 0.7910 0.00819 0.00233 -0.0834 0.2730 0.7908
3.750 0.8180 0.00840 0.00247 -0.0832 0.2572 0.7944
4.000 0.8448 0.00859 0.00262 -0.0831 0.2421 0.7979
4.250 0.8715 0.00879 0.00277 -0.0829 0.2281 0.8018
4.500 0.8980 0.00903 0.00294 -0.0827 0.2121 0.8059
5.000 0.9507 0.00950 0.00332 -0.0822 0.1833 0.8141
5.250 0.9768 0.00976 0.00352 -0.0820 0.1693 0.8188
5.500 1.0027 0.01003 0.00374 -0.0817 0.1551 0.8236
5.750 1.0286 0.01028 0.00397 -0.0814 0.1435 0.8287
6.000 1.0542 0.01054 0.00420 -0.0811 0.1323 0.8347
6.500 1.1049 0.01111 0.00472 -0.0804 0.1114 0.8482
6.750 1.1303 0.01135 0.00497 -0.0801 0.1036 0.8572
7.000 1.1549 0.01163 0.00525 -0.0796 0.0950 0.8694
7.250 1.1783 0.01192 0.00556 -0.0789 0.0859 0.8879
7.500 1.2009 0.01202 0.00579 -0.0778 0.0801 0.9910
7.750 1.2255 0.01239 0.00612 -0.0774 0.0728 1.0000
8.000 1.2501 0.01275 0.00646 -0.0771 0.0662 1.0000
8.250 1.2745 0.01312 0.00681 -0.0766 0.0607 1.0000
8.500 1.2986 0.01350 0.00718 -0.0762 0.0555 1.0000
8.750 1.3224 0.01390 0.00756 -0.0757 0.0506 1.0000
9.000 1.3460 0.01429 0.00795 -0.0751 0.0467 1.0000
9.250 1.3690 0.01473 0.00839 -0.0745 0.0428 1.0000
9.500 1.3923 0.01511 0.00879 -0.0740 0.0403 1.0000
9.750 1.4146 0.01557 0.00925 -0.0733 0.0373 1.0000
10.000 1.4366 0.01603 0.00972 -0.0725 0.0348 1.0000
10.250 1.4588 0.01645 0.01018 -0.0718 0.0331 1.0000
10.500 1.4800 0.01692 0.01067 -0.0710 0.0311 1.0000
10.750 1.5002 0.01746 0.01122 -0.0700 0.0291 1.0000
11.000 1.5205 0.01795 0.01175 -0.0690 0.0277 1.0000
11.250 1.5404 0.01844 0.01228 -0.0680 0.0265 1.0000
11.500 1.5591 0.01897 0.01285 -0.0669 0.0252 1.0000
11.750 1.5761 0.01958 0.01349 -0.0654 0.0239 1.0000
12.000 1.5900 0.02022 0.01416 -0.0635 0.0225 1.0000
12.250 1.6043 0.02076 0.01476 -0.0616 0.0217 1.0000
12.500 1.6171 0.02139 0.01544 -0.0596 0.0204 1.0000
12.750 1.6281 0.02216 0.01624 -0.0575 0.0189 1.0000
13.000 1.6385 0.02300 0.01712 -0.0554 0.0178 1.0000
13.250 1.6500 0.02381 0.01799 -0.0536 0.0171 1.0000
13.500 1.6603 0.02472 0.01896 -0.0518 0.0164 1.0000
13.750 1.6694 0.02576 0.02005 -0.0501 0.0154 1.0000
14.000 1.6769 0.02696 0.02130 -0.0483 0.0145 1.0000
14.250 1.6848 0.02820 0.02261 -0.0467 0.0138 1.0000
14.500 1.6924 0.02950 0.02399 -0.0453 0.0131 1.0000
14.750 1.6988 0.03098 0.02554 -0.0439 0.0125 1.0000
15.000 1.7035 0.03266 0.02728 -0.0426 0.0117 1.0000
15.250 1.7067 0.03455 0.02924 -0.0415 0.0110 1.0000
15.500 1.7108 0.03644 0.03123 -0.0405 0.0106 1.0000
15.750 1.7138 0.03854 0.03341 -0.0398 0.0102 1.0000
16.000 1.7152 0.04089 0.03585 -0.0392 0.0096 1.0000
16.250 1.7151 0.04351 0.03856 -0.0388 0.0092 1.0000
16.500 1.7131 0.04649 0.04163 -0.0387 0.0087 1.0000
16.750 1.7095 0.04979 0.04503 -0.0389 0.0084 1.0000
17.000 1.7063 0.05321 0.04856 -0.0393 0.0081 1.0000
17.250 1.7017 0.05700 0.05247 -0.0401 0.0078 1.0000
17.500 1.6952 0.06123 0.05682 -0.0412 0.0075 1.0000
17.750 1.6869 0.06594 0.06165 -0.0428 0.0073 1.0000
18.000 1.6767 0.07119 0.06702 -0.0448 0.0071 1.0000
18.250 1.6639 0.07703 0.07300 -0.0472 0.0069 1.0000
18.500 1.6489 0.08351 0.07961 -0.0501 0.0067 1.0000
18.750 1.6316 0.09061 0.08685 -0.0536 0.0065 1.0000
19.000 1.6121 0.09832 0.09470 -0.0575 0.0064 1.0000
19.250 1.5912 0.10654 0.10308 -0.0618 0.0063 1.0000
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Polar data table (+)
Polar graphs
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