SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.49 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7062-il-1000000-n5.txt Download as CSV file: xf-sd7062-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7062 (14%)
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7847 0.05436 0.05160 -0.0715 1.0000 0.0107
-13.750 -0.8129 0.04574 0.04280 -0.0784 1.0000 0.0107
-13.500 -0.8281 0.03960 0.03650 -0.0837 1.0000 0.0107
-13.250 -0.8415 0.03454 0.03129 -0.0879 1.0000 0.0107
-13.000 -0.8541 0.03103 0.02764 -0.0897 1.0000 0.0107
-12.750 -0.8594 0.02866 0.02515 -0.0900 0.9900 0.0108
-12.500 -0.8350 0.02662 0.02294 -0.0934 0.9779 0.0109
-12.250 -0.8089 0.02488 0.02105 -0.0961 0.9628 0.0109
-12.000 -0.7857 0.02357 0.01957 -0.0973 0.9416 0.0110
-11.750 -0.7702 0.02249 0.01832 -0.0965 0.9161 0.0111
-11.500 -0.7544 0.02162 0.01727 -0.0953 0.8935 0.0112
-11.250 -0.7372 0.02078 0.01628 -0.0943 0.8753 0.0112
-11.000 -0.7182 0.02003 0.01538 -0.0934 0.8597 0.0113
-10.750 -0.6977 0.01935 0.01456 -0.0926 0.8460 0.0114
-10.500 -0.6761 0.01874 0.01382 -0.0919 0.8340 0.0115
-10.250 -0.6534 0.01817 0.01314 -0.0914 0.8222 0.0115
-10.000 -0.6330 0.01722 0.01207 -0.0907 0.8117 0.0117
-9.750 -0.6105 0.01655 0.01130 -0.0901 0.8008 0.0119
-9.500 -0.5864 0.01600 0.01067 -0.0897 0.7910 0.0120
-9.250 -0.5621 0.01550 0.01007 -0.0893 0.7812 0.0122
-9.000 -0.5368 0.01504 0.00955 -0.0889 0.7719 0.0123
-8.750 -0.5115 0.01462 0.00905 -0.0886 0.7628 0.0124
-8.500 -0.4858 0.01419 0.00855 -0.0883 0.7537 0.0126
-8.250 -0.4599 0.01381 0.00808 -0.0880 0.7447 0.0127
-8.000 -0.4336 0.01342 0.00763 -0.0877 0.7356 0.0129
-7.750 -0.4073 0.01306 0.00719 -0.0874 0.7268 0.0131
-7.500 -0.3806 0.01271 0.00678 -0.0872 0.7177 0.0133
-7.250 -0.3539 0.01239 0.00638 -0.0870 0.7092 0.0134
-7.000 -0.3268 0.01207 0.00600 -0.0868 0.7002 0.0136
-6.750 -0.2997 0.01179 0.00565 -0.0866 0.6916 0.0138
-6.500 -0.2723 0.01151 0.00532 -0.0864 0.6825 0.0140
-6.250 -0.2449 0.01128 0.00501 -0.0862 0.6737 0.0142
-6.000 -0.2172 0.01103 0.00472 -0.0861 0.6648 0.0143
-5.750 -0.1901 0.01070 0.00433 -0.0859 0.6562 0.0147
-5.500 -0.1623 0.01045 0.00403 -0.0858 0.6471 0.0150
-5.250 -0.1346 0.01025 0.00379 -0.0856 0.6381 0.0154
-5.000 -0.1065 0.01007 0.00356 -0.0855 0.6290 0.0157
-4.750 -0.0785 0.00991 0.00336 -0.0854 0.6201 0.0162
-4.500 -0.0503 0.00977 0.00317 -0.0853 0.6104 0.0167
-4.250 -0.0221 0.00965 0.00300 -0.0852 0.6016 0.0172
-4.000 0.0060 0.00949 0.00280 -0.0851 0.5919 0.0177
-3.750 0.0343 0.00935 0.00262 -0.0851 0.5830 0.0184
-3.500 0.0625 0.00925 0.00248 -0.0850 0.5730 0.0193
-3.250 0.0909 0.00915 0.00235 -0.0849 0.5640 0.0202
-3.000 0.1191 0.00907 0.00222 -0.0848 0.5540 0.0217
-2.750 0.1476 0.00898 0.00211 -0.0848 0.5449 0.0242
-2.500 0.1757 0.00887 0.00200 -0.0847 0.5354 0.0314
-2.250 0.2039 0.00872 0.00190 -0.0847 0.5260 0.0501
-2.000 0.2321 0.00860 0.00182 -0.0846 0.5169 0.0691
-1.750 0.2603 0.00849 0.00175 -0.0846 0.5071 0.0906
-1.500 0.2885 0.00839 0.00170 -0.0846 0.4982 0.1157
-1.250 0.3165 0.00825 0.00165 -0.0846 0.4884 0.1553
-1.000 0.3446 0.00811 0.00161 -0.0846 0.4795 0.1988
-0.750 0.3725 0.00801 0.00160 -0.0846 0.4698 0.2443
-0.500 0.4006 0.00788 0.00159 -0.0846 0.4606 0.2929
-0.250 0.4285 0.00781 0.00160 -0.0846 0.4511 0.3392
0.000 0.4565 0.00769 0.00162 -0.0846 0.4419 0.3972
0.250 0.4845 0.00767 0.00166 -0.0845 0.4326 0.4362
0.500 0.5126 0.00767 0.00169 -0.0845 0.4232 0.4649
0.750 0.5406 0.00769 0.00174 -0.0844 0.4141 0.4949
1.000 0.5686 0.00771 0.00180 -0.0844 0.4051 0.5261
1.250 0.5966 0.00774 0.00186 -0.0843 0.3964 0.5526
1.500 0.6244 0.00779 0.00193 -0.0842 0.3870 0.5772
1.750 0.6523 0.00784 0.00199 -0.0841 0.3789 0.6021
2.000 0.6799 0.00791 0.00208 -0.0840 0.3697 0.6266
2.250 0.7077 0.00795 0.00216 -0.0839 0.3615 0.6528
2.500 0.7350 0.00804 0.00226 -0.0837 0.3529 0.6792
2.750 0.7625 0.00809 0.00236 -0.0836 0.3446 0.7072
3.000 0.7894 0.00818 0.00247 -0.0833 0.3357 0.7353
3.250 0.8165 0.00823 0.00258 -0.0831 0.3281 0.7651
3.500 0.8428 0.00833 0.00271 -0.0827 0.3194 0.7964
3.750 0.8690 0.00838 0.00283 -0.0823 0.3118 0.8307
4.000 0.8935 0.00846 0.00297 -0.0815 0.3035 0.8703
4.250 0.9164 0.00847 0.00308 -0.0803 0.2964 0.9214
4.500 0.9494 0.00859 0.00321 -0.0813 0.2877 1.0000
4.750 0.9765 0.00875 0.00333 -0.0812 0.2804 1.0000
5.250 1.0296 0.00914 0.00364 -0.0808 0.2651 1.0000
5.500 1.0556 0.00937 0.00381 -0.0805 0.2566 1.0000
5.750 1.0821 0.00955 0.00396 -0.0802 0.2504 1.0000
6.000 1.1078 0.00979 0.00415 -0.0799 0.2425 1.0000
6.250 1.1338 0.00999 0.00433 -0.0796 0.2358 1.0000
6.500 1.1594 0.01022 0.00453 -0.0793 0.2291 1.0000
6.750 1.1848 0.01045 0.00473 -0.0789 0.2228 1.0000
7.000 1.2099 0.01070 0.00495 -0.0785 0.2153 1.0000
7.250 1.2346 0.01096 0.00518 -0.0781 0.2091 1.0000
7.500 1.2596 0.01119 0.00540 -0.0777 0.2032 1.0000
7.750 1.2831 0.01151 0.00567 -0.0770 0.1956 1.0000
8.000 1.3077 0.01174 0.00589 -0.0766 0.1909 1.0000
8.250 1.3311 0.01204 0.00617 -0.0759 0.1845 1.0000
8.500 1.3542 0.01234 0.00645 -0.0753 0.1786 1.0000
8.750 1.3772 0.01263 0.00673 -0.0746 0.1729 1.0000
9.000 1.3987 0.01299 0.00706 -0.0737 0.1668 1.0000
9.250 1.4210 0.01328 0.00735 -0.0729 0.1616 1.0000
9.500 1.4414 0.01365 0.00770 -0.0718 0.1558 1.0000
9.750 1.4619 0.01400 0.00804 -0.0708 0.1510 1.0000
10.000 1.4805 0.01435 0.00839 -0.0694 0.1457 1.0000
10.250 1.4957 0.01479 0.00880 -0.0674 0.1401 1.0000
10.500 1.5125 0.01515 0.00918 -0.0658 0.1361 1.0000
10.750 1.5274 0.01560 0.00963 -0.0639 0.1312 1.0000
11.000 1.5415 0.01612 0.01013 -0.0620 0.1264 1.0000
11.250 1.5564 0.01661 0.01064 -0.0603 0.1219 1.0000
11.500 1.5692 0.01723 0.01125 -0.0584 0.1172 1.0000
11.750 1.5828 0.01782 0.01186 -0.0567 0.1134 1.0000
12.000 1.5959 0.01847 0.01252 -0.0550 0.1094 1.0000
12.250 1.6069 0.01926 0.01332 -0.0532 0.1052 1.0000
12.500 1.6189 0.02004 0.01412 -0.0516 0.1018 1.0000
12.750 1.6305 0.02088 0.01498 -0.0501 0.0983 1.0000
13.000 1.6399 0.02189 0.01600 -0.0485 0.0945 1.0000
13.250 1.6496 0.02294 0.01707 -0.0471 0.0910 1.0000
13.500 1.6597 0.02400 0.01816 -0.0458 0.0880 1.0000
13.750 1.6672 0.02529 0.01947 -0.0445 0.0845 1.0000
14.000 1.6747 0.02664 0.02085 -0.0432 0.0816 1.0000
14.250 1.6837 0.02793 0.02219 -0.0422 0.0793 1.0000
14.500 1.6904 0.02945 0.02374 -0.0412 0.0765 1.0000
14.750 1.6950 0.03119 0.02551 -0.0402 0.0738 1.0000
15.000 1.7006 0.03291 0.02728 -0.0393 0.0713 1.0000
15.250 1.7056 0.03475 0.02916 -0.0386 0.0688 1.0000
15.500 1.7082 0.03685 0.03130 -0.0380 0.0664 1.0000
15.750 1.7089 0.03922 0.03371 -0.0374 0.0638 1.0000
16.000 1.7130 0.04134 0.03590 -0.0370 0.0623 1.0000
16.250 1.7141 0.04384 0.03846 -0.0368 0.0598 1.0000
16.500 1.7116 0.04680 0.04146 -0.0367 0.0572 1.0000
16.750 1.7103 0.04974 0.04446 -0.0367 0.0551 1.0000
17.000 1.7097 0.05270 0.04748 -0.0369 0.0533 1.0000
17.250 1.7065 0.05603 0.05088 -0.0373 0.0513 1.0000
17.500 1.7002 0.05986 0.05476 -0.0379 0.0491 1.0000
17.750 1.6969 0.06343 0.05840 -0.0386 0.0474 1.0000
18.000 1.6928 0.06715 0.06221 -0.0394 0.0460 1.0000
18.250 1.6865 0.07129 0.06642 -0.0404 0.0446 1.0000
18.500 1.6775 0.07589 0.07109 -0.0417 0.0430 1.0000
18.750 1.6705 0.08030 0.07559 -0.0431 0.0420 1.0000
19.000 1.6634 0.08482 0.08019 -0.0446 0.0406 1.0000
19.250 1.6547 0.08966 0.08512 -0.0463 0.0393 1.0000
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Polar data table (+)
Polar graphs
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