S2046 (s2046-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 500,000 Max Cl/Cd: 84.84 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2046-il-500000-n5.txt Download as CSV file: xf-s2046-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2046
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4814 0.10070 0.09821 -0.0253 1.0000 0.0101
-10.500 -0.6766 0.04981 0.04714 -0.0555 1.0000 0.0092
-10.250 -0.7089 0.04088 0.03803 -0.0645 1.0000 0.0091
-10.000 -0.7164 0.03604 0.03290 -0.0686 1.0000 0.0091
-9.750 -0.7139 0.03282 0.02941 -0.0695 1.0000 0.0092
-9.500 -0.7125 0.02893 0.02513 -0.0699 1.0000 0.0093
-9.250 -0.6949 0.02549 0.02130 -0.0719 0.9983 0.0095
-9.000 -0.6664 0.02304 0.01856 -0.0746 0.9954 0.0097
-8.750 -0.6369 0.02131 0.01662 -0.0766 0.9927 0.0099
-8.500 -0.6073 0.01995 0.01507 -0.0782 0.9896 0.0101
-8.250 -0.5765 0.01876 0.01372 -0.0797 0.9867 0.0104
-8.000 -0.5446 0.01766 0.01246 -0.0814 0.9845 0.0107
-7.750 -0.5126 0.01666 0.01132 -0.0829 0.9822 0.0110
-7.500 -0.4832 0.01579 0.01031 -0.0837 0.9781 0.0113
-7.250 -0.4520 0.01495 0.00934 -0.0849 0.9747 0.0116
-7.000 -0.4199 0.01420 0.00848 -0.0861 0.9718 0.0119
-6.750 -0.3884 0.01352 0.00770 -0.0872 0.9684 0.0122
-6.500 -0.3592 0.01296 0.00706 -0.0877 0.9629 0.0125
-6.250 -0.3278 0.01238 0.00640 -0.0886 0.9587 0.0129
-6.000 -0.2967 0.01170 0.00566 -0.0896 0.9544 0.0138
-5.750 -0.2678 0.01124 0.00514 -0.0899 0.9480 0.0144
-5.500 -0.2371 0.01082 0.00466 -0.0905 0.9428 0.0151
-5.250 -0.2080 0.01046 0.00425 -0.0908 0.9364 0.0160
-5.000 -0.1787 0.01015 0.00386 -0.0910 0.9299 0.0168
-4.750 -0.1498 0.00981 0.00348 -0.0912 0.9234 0.0188
-4.500 -0.1213 0.00952 0.00317 -0.0913 0.9164 0.0225
-4.250 -0.0930 0.00920 0.00290 -0.0913 0.9097 0.0349
-4.000 -0.0650 0.00897 0.00269 -0.0913 0.9023 0.0478
-3.750 -0.0370 0.00878 0.00251 -0.0913 0.8950 0.0585
-3.500 -0.0091 0.00860 0.00235 -0.0912 0.8867 0.0699
-3.250 0.0187 0.00844 0.00219 -0.0911 0.8779 0.0809
-3.000 0.0463 0.00829 0.00204 -0.0909 0.8676 0.0937
-2.750 0.0738 0.00813 0.00190 -0.0907 0.8553 0.1132
-2.500 0.1013 0.00794 0.00175 -0.0906 0.8423 0.1383
-2.250 0.1289 0.00777 0.00163 -0.0904 0.8298 0.1664
-2.000 0.1567 0.00760 0.00151 -0.0903 0.8179 0.2019
-1.750 0.1844 0.00737 0.00141 -0.0903 0.8061 0.2551
-1.500 0.2120 0.00707 0.00132 -0.0904 0.7942 0.3387
-1.000 0.2674 0.00674 0.00128 -0.0902 0.7698 0.4694
-0.750 0.2952 0.00669 0.00127 -0.0901 0.7569 0.5041
-0.500 0.3229 0.00668 0.00127 -0.0899 0.7436 0.5300
-0.250 0.3505 0.00668 0.00128 -0.0897 0.7290 0.5530
0.000 0.3781 0.00671 0.00129 -0.0894 0.7136 0.5726
0.250 0.4054 0.00673 0.00132 -0.0891 0.6967 0.5987
0.500 0.4325 0.00676 0.00137 -0.0888 0.6779 0.6292
0.750 0.4596 0.00681 0.00143 -0.0885 0.6573 0.6538
1.000 0.4864 0.00691 0.00148 -0.0881 0.6343 0.6719
1.250 0.5132 0.00702 0.00153 -0.0877 0.6080 0.6855
1.500 0.5397 0.00717 0.00161 -0.0873 0.5791 0.6981
1.750 0.5660 0.00736 0.00169 -0.0869 0.5464 0.7107
2.000 0.5921 0.00758 0.00180 -0.0865 0.5113 0.7237
2.250 0.6178 0.00783 0.00194 -0.0860 0.4745 0.7369
2.500 0.6434 0.00810 0.00208 -0.0856 0.4357 0.7506
2.750 0.6685 0.00843 0.00225 -0.0850 0.3920 0.7650
3.000 0.6938 0.00873 0.00243 -0.0846 0.3558 0.7803
3.500 0.7448 0.00920 0.00278 -0.0836 0.3003 0.8154
3.750 0.7700 0.00937 0.00295 -0.0830 0.2801 0.8384
4.000 0.7934 0.00952 0.00312 -0.0820 0.2569 0.8744
4.250 0.8196 0.00966 0.00328 -0.0816 0.2309 1.0000
4.500 0.8456 0.01003 0.00352 -0.0814 0.2034 1.0000
4.750 0.8711 0.01044 0.00378 -0.0810 0.1739 1.0000
5.000 0.8965 0.01085 0.00406 -0.0807 0.1474 1.0000
5.250 0.9216 0.01129 0.00439 -0.0803 0.1228 1.0000
5.750 0.9717 0.01219 0.00509 -0.0795 0.0841 1.0000
6.000 0.9969 0.01260 0.00544 -0.0791 0.0728 1.0000
6.250 1.0222 0.01299 0.00581 -0.0787 0.0646 1.0000
6.500 1.0475 0.01336 0.00617 -0.0783 0.0584 1.0000
6.750 1.0723 0.01378 0.00657 -0.0779 0.0522 1.0000
7.000 1.0973 0.01416 0.00697 -0.0775 0.0481 1.0000
7.250 1.1221 0.01456 0.00740 -0.0770 0.0447 1.0000
7.500 1.1462 0.01504 0.00787 -0.0764 0.0410 1.0000
7.750 1.1704 0.01547 0.00834 -0.0759 0.0386 1.0000
8.000 1.1946 0.01588 0.00880 -0.0753 0.0364 1.0000
8.250 1.2183 0.01635 0.00930 -0.0747 0.0342 1.0000
8.500 1.2411 0.01691 0.00988 -0.0740 0.0319 1.0000
8.750 1.2639 0.01744 0.01045 -0.0733 0.0299 1.0000
9.000 1.2873 0.01786 0.01094 -0.0727 0.0281 1.0000
9.250 1.3099 0.01836 0.01146 -0.0720 0.0260 1.0000
9.500 1.3314 0.01897 0.01209 -0.0712 0.0242 1.0000
9.750 1.3523 0.01962 0.01281 -0.0702 0.0229 1.0000
10.000 1.3738 0.02015 0.01343 -0.0694 0.0218 1.0000
10.250 1.3947 0.02072 0.01406 -0.0685 0.0204 1.0000
10.500 1.4149 0.02133 0.01471 -0.0675 0.0190 1.0000
10.750 1.4330 0.02212 0.01553 -0.0663 0.0174 1.0000
11.000 1.4521 0.02274 0.01624 -0.0651 0.0165 1.0000
11.250 1.4701 0.02343 0.01701 -0.0639 0.0153 1.0000
11.500 1.4868 0.02419 0.01784 -0.0625 0.0142 1.0000
11.750 1.5007 0.02506 0.01876 -0.0607 0.0132 1.0000
12.000 1.5124 0.02592 0.01971 -0.0585 0.0124 1.0000
12.250 1.5229 0.02682 0.02071 -0.0563 0.0117 1.0000
12.500 1.5323 0.02780 0.02179 -0.0541 0.0110 1.0000
12.750 1.5405 0.02891 0.02298 -0.0519 0.0103 1.0000
13.000 1.5464 0.03024 0.02438 -0.0497 0.0097 1.0000
13.250 1.5513 0.03170 0.02595 -0.0476 0.0093 1.0000
13.500 1.5564 0.03322 0.02761 -0.0458 0.0089 1.0000
13.750 1.5607 0.03487 0.02939 -0.0441 0.0085 1.0000
14.000 1.5639 0.03673 0.03136 -0.0427 0.0081 1.0000
14.250 1.5654 0.03883 0.03359 -0.0415 0.0078 1.0000
14.500 1.5656 0.04121 0.03609 -0.0405 0.0075 1.0000
14.750 1.5638 0.04395 0.03895 -0.0399 0.0073 1.0000
15.000 1.5592 0.04718 0.04231 -0.0396 0.0070 1.0000
15.250 1.5520 0.05098 0.04625 -0.0399 0.0069 1.0000
15.500 1.5419 0.05544 0.05087 -0.0408 0.0067 1.0000
15.750 1.5329 0.06008 0.05567 -0.0422 0.0066 1.0000
16.000 1.5220 0.06533 0.06109 -0.0442 0.0066 1.0000
16.250 1.5087 0.07140 0.06733 -0.0469 0.0065 1.0000
16.500 1.4930 0.07828 0.07439 -0.0504 0.0065 1.0000
16.750 1.4744 0.08611 0.08240 -0.0546 0.0065 1.0000
17.000 1.4538 0.09468 0.09114 -0.0594 0.0065 1.0000
17.250 1.4301 0.10417 0.10081 -0.0648 0.0065 1.0000
17.500 1.4050 0.11426 0.11107 -0.0707 0.0065 1.0000
17.750 1.3792 0.12474 0.12171 -0.0769 0.0065 1.0000
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