NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 50,000 Max Cl/Cd: 35.91 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413-il-50000.txt Download as CSV file: xf-ls413-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3907 0.11981 0.11232 -0.0277 1.0000 0.3031
-10.000 -0.3723 0.11561 0.10814 -0.0269 1.0000 0.3127
-9.500 -0.3980 0.11304 0.10580 -0.0250 1.0000 0.3374
-9.250 -0.3762 0.10902 0.10178 -0.0236 1.0000 0.3518
-9.000 -0.3625 0.10546 0.09824 -0.0224 1.0000 0.3621
-8.500 -0.3805 0.10210 0.09510 -0.0183 1.0000 0.3879
-8.250 -0.3646 0.09866 0.09167 -0.0170 1.0000 0.3969
-8.000 -0.3711 0.09663 0.08974 -0.0146 1.0000 0.4075
-7.000 -0.6057 0.06059 0.05311 -0.0441 1.0000 0.1599
-6.750 -0.5916 0.05682 0.04921 -0.0441 1.0000 0.1545
-6.500 -0.5733 0.05116 0.04244 -0.0480 1.0000 0.1426
-6.250 -0.5535 0.04772 0.03885 -0.0483 1.0000 0.1406
-6.000 -0.5307 0.04446 0.03524 -0.0492 1.0000 0.1378
-5.750 -0.5050 0.04149 0.03181 -0.0501 1.0000 0.1353
-5.500 -0.4776 0.03896 0.02883 -0.0509 1.0000 0.1342
-5.250 -0.4506 0.03698 0.02650 -0.0513 1.0000 0.1359
-5.000 -0.4235 0.03537 0.02452 -0.0515 1.0000 0.1398
-4.750 -0.3965 0.03390 0.02272 -0.0514 1.0000 0.1437
-4.500 -0.3725 0.03247 0.02135 -0.0506 1.0000 0.1486
-4.250 -0.3482 0.03151 0.02026 -0.0497 1.0000 0.1571
-4.000 -0.3259 0.03051 0.01939 -0.0484 1.0000 0.1689
-3.750 -0.3029 0.02958 0.01856 -0.0471 1.0000 0.1846
-3.500 -0.2771 0.02842 0.01768 -0.0470 1.0000 0.2183
-3.000 -0.2729 0.02819 0.02047 -0.0295 1.0000 0.7487
-2.750 -0.2795 0.02896 0.02114 -0.0196 1.0000 0.7969
-2.500 -0.2836 0.02918 0.02126 -0.0109 1.0000 0.8381
-2.250 -0.1270 0.03035 0.02167 -0.0231 1.0000 1.0000
-2.000 -0.1273 0.02995 0.02116 -0.0205 1.0000 1.0000
-1.750 -0.1270 0.02957 0.02068 -0.0179 1.0000 1.0000
-1.500 -0.1262 0.02920 0.02023 -0.0153 1.0000 1.0000
-1.250 -0.1248 0.02886 0.01979 -0.0128 1.0000 1.0000
-1.000 -0.1225 0.02853 0.01938 -0.0103 1.0000 1.0000
-0.750 -0.1190 0.02824 0.01902 -0.0081 1.0000 1.0000
-0.500 -0.1111 0.02807 0.01876 -0.0067 1.0000 1.0000
-0.250 -0.0971 0.02808 0.01868 -0.0063 1.0000 1.0000
0.000 -0.0783 0.02827 0.01876 -0.0068 1.0000 1.0000
0.250 -0.0560 0.02861 0.01901 -0.0079 1.0000 1.0000
0.500 -0.0316 0.02907 0.01939 -0.0095 1.0000 1.0000
0.750 -0.0059 0.02964 0.01988 -0.0113 1.0000 1.0000
1.000 0.0206 0.03030 0.02048 -0.0132 1.0000 1.0000
1.250 0.0474 0.03104 0.02118 -0.0153 1.0000 1.0000
1.500 0.0743 0.03187 0.02197 -0.0174 1.0000 1.0000
1.750 0.1011 0.03277 0.02286 -0.0195 1.0000 1.0000
2.000 0.1276 0.03376 0.02384 -0.0217 1.0000 1.0000
2.250 0.1536 0.03482 0.02492 -0.0238 1.0000 1.0000
2.500 0.1790 0.03597 0.02609 -0.0260 1.0000 1.0000
2.750 0.2077 0.03730 0.02746 -0.0288 0.9975 1.0000
3.000 0.2869 0.03974 0.02995 -0.0402 0.9655 1.0000
3.500 0.3932 0.04258 0.03297 -0.0523 0.9146 1.0000
3.750 0.4466 0.04361 0.03413 -0.0575 0.8878 1.0000
4.000 0.5069 0.04404 0.03470 -0.0627 0.8577 1.0000
4.250 0.5698 0.04372 0.03457 -0.0671 0.8277 1.0000
4.500 0.6137 0.04329 0.03431 -0.0686 0.7981 1.0000
4.750 0.6634 0.04221 0.03346 -0.0699 0.7685 1.0000
5.000 0.7189 0.04006 0.03155 -0.0706 0.7382 1.0000
5.250 0.7766 0.03679 0.02859 -0.0702 0.7076 1.0000
5.500 0.8372 0.03238 0.02448 -0.0688 0.6721 1.0000
5.750 0.8869 0.02822 0.02050 -0.0657 0.6090 1.0000
6.000 0.9343 0.02602 0.01723 -0.0625 0.4703 1.0000
6.250 0.9576 0.02782 0.01811 -0.0610 0.3871 1.0000
6.500 0.9881 0.02966 0.01948 -0.0614 0.3371 1.0000
6.750 1.0212 0.03142 0.02095 -0.0623 0.3032 1.0000
7.000 1.0578 0.03333 0.02263 -0.0638 0.2783 1.0000
7.250 1.0879 0.03522 0.02455 -0.0644 0.2589 1.0000
7.500 1.1186 0.03727 0.02663 -0.0652 0.2439 1.0000
7.750 1.1475 0.03936 0.02872 -0.0657 0.2304 1.0000
8.000 1.1727 0.04154 0.03111 -0.0657 0.2195 1.0000
8.250 1.1936 0.04405 0.03392 -0.0651 0.2103 1.0000
8.500 1.2230 0.04661 0.03634 -0.0659 0.2008 1.0000
8.750 1.2314 0.04949 0.03989 -0.0636 0.1952 1.0000
9.000 1.2531 0.05205 0.04255 -0.0633 0.1875 1.0000
9.250 1.2619 0.05553 0.04641 -0.0616 0.1829 1.0000
9.500 1.2605 0.05928 0.05070 -0.0588 0.1799 1.0000
9.750 1.2585 0.06303 0.05485 -0.0562 0.1767 1.0000
10.000 1.2912 0.06620 0.05778 -0.0575 0.1697 1.0000
10.250 1.2759 0.07055 0.06264 -0.0539 0.1690 1.0000
10.500 1.2572 0.07526 0.06775 -0.0507 0.1688 1.0000
10.750 1.2352 0.08020 0.07299 -0.0477 0.1690 1.0000
11.000 1.2107 0.08517 0.07818 -0.0449 0.1694 1.0000
11.250 0.9681 0.11754 0.11095 -0.0596 0.2035 1.0000
11.500 0.9819 0.12121 0.11467 -0.0589 0.2013 1.0000
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Polar data table (+)
Polar graphs
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