NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 500,000 Max Cl/Cd: 77.57 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413mod-il-500000-n5.txt Download as CSV file: xf-ls413mod-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413MOD AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7713 0.06169 0.05854 -0.0582 1.0000 0.0160
-13.250 -0.7991 0.05345 0.05007 -0.0647 1.0000 0.0160
-13.000 -0.8194 0.04765 0.04406 -0.0682 1.0000 0.0160
-12.750 -0.8345 0.04328 0.03947 -0.0699 1.0000 0.0160
-12.500 -0.8465 0.03984 0.03583 -0.0701 1.0000 0.0160
-12.250 -0.8585 0.03728 0.03310 -0.0685 1.0000 0.0160
-12.000 -0.8637 0.03494 0.03057 -0.0673 1.0000 0.0161
-11.750 -0.8631 0.03292 0.02834 -0.0657 1.0000 0.0161
-11.500 -0.8588 0.03116 0.02640 -0.0640 1.0000 0.0162
-11.250 -0.8419 0.02928 0.02430 -0.0644 0.9982 0.0162
-11.000 -0.8160 0.02751 0.02229 -0.0662 0.9952 0.0163
-10.750 -0.7891 0.02591 0.02050 -0.0678 0.9924 0.0164
-10.500 -0.7632 0.02415 0.01858 -0.0692 0.9887 0.0166
-10.250 -0.7342 0.02282 0.01714 -0.0707 0.9856 0.0168
-10.000 -0.7031 0.02170 0.01593 -0.0725 0.9829 0.0169
-9.750 -0.6745 0.02076 0.01491 -0.0735 0.9774 0.0171
-9.500 -0.6441 0.01987 0.01394 -0.0749 0.9727 0.0173
-9.250 -0.6131 0.01904 0.01304 -0.0762 0.9686 0.0175
-9.000 -0.5844 0.01828 0.01221 -0.0770 0.9623 0.0177
-8.750 -0.5537 0.01754 0.01140 -0.0781 0.9570 0.0179
-8.500 -0.5246 0.01686 0.01065 -0.0789 0.9500 0.0182
-8.250 -0.4951 0.01620 0.00993 -0.0796 0.9426 0.0185
-8.000 -0.4666 0.01560 0.00927 -0.0801 0.9348 0.0188
-7.750 -0.4380 0.01504 0.00864 -0.0806 0.9264 0.0191
-7.500 -0.4099 0.01453 0.00806 -0.0810 0.9176 0.0194
-7.250 -0.3816 0.01407 0.00753 -0.0813 0.9089 0.0197
-7.000 -0.3533 0.01370 0.00710 -0.0816 0.8997 0.0201
-6.750 -0.3251 0.01311 0.00648 -0.0820 0.8912 0.0207
-6.500 -0.2965 0.01271 0.00605 -0.0824 0.8821 0.0213
-6.250 -0.2677 0.01237 0.00566 -0.0828 0.8739 0.0219
-6.000 -0.2386 0.01203 0.00528 -0.0832 0.8650 0.0225
-5.750 -0.2094 0.01174 0.00493 -0.0837 0.8571 0.0232
-5.500 -0.1799 0.01147 0.00460 -0.0841 0.8484 0.0240
-5.250 -0.1503 0.01118 0.00427 -0.0846 0.8405 0.0249
-5.000 -0.1204 0.01089 0.00395 -0.0852 0.8320 0.0262
-4.750 -0.0907 0.01068 0.00369 -0.0856 0.8242 0.0278
-4.500 -0.0607 0.01048 0.00346 -0.0861 0.8155 0.0299
-4.250 -0.0307 0.01027 0.00324 -0.0867 0.8073 0.0339
-4.000 -0.0004 0.01004 0.00305 -0.0873 0.7980 0.0446
-3.750 0.0299 0.00983 0.00287 -0.0879 0.7889 0.0628
-3.500 0.0606 0.00956 0.00270 -0.0887 0.7793 0.0935
-3.250 0.0924 0.00916 0.00253 -0.0899 0.7708 0.1590
-3.000 0.1246 0.00875 0.00237 -0.0913 0.7627 0.2386
-2.750 0.1579 0.00827 0.00222 -0.0930 0.7553 0.3386
-2.500 0.1916 0.00781 0.00210 -0.0947 0.7477 0.4465
-2.250 0.2251 0.00744 0.00209 -0.0962 0.7401 0.5553
-2.000 0.2559 0.00737 0.00215 -0.0968 0.7316 0.6091
-1.750 0.2859 0.00739 0.00220 -0.0972 0.7236 0.6396
-1.500 0.3157 0.00745 0.00225 -0.0974 0.7140 0.6643
-1.250 0.3452 0.00752 0.00229 -0.0976 0.7018 0.6790
-1.000 0.3742 0.00759 0.00231 -0.0977 0.6863 0.6869
-0.750 0.4036 0.00769 0.00232 -0.0979 0.6705 0.6961
-0.500 0.4325 0.00776 0.00236 -0.0980 0.6575 0.7023
-0.250 0.4618 0.00784 0.00239 -0.0982 0.6456 0.7063
0.000 0.4912 0.00792 0.00240 -0.0985 0.6304 0.7102
0.250 0.5201 0.00804 0.00243 -0.0986 0.6100 0.7143
0.500 0.5483 0.00818 0.00249 -0.0986 0.5853 0.7187
0.750 0.5766 0.00835 0.00256 -0.0987 0.5611 0.7238
1.000 0.6053 0.00852 0.00262 -0.0988 0.5380 0.7286
1.250 0.6333 0.00871 0.00272 -0.0989 0.5131 0.7324
1.500 0.6612 0.00890 0.00283 -0.0989 0.4892 0.7361
1.750 0.6891 0.00913 0.00296 -0.0989 0.4632 0.7396
2.000 0.7167 0.00940 0.00309 -0.0989 0.4344 0.7428
2.250 0.7445 0.00967 0.00324 -0.0990 0.4071 0.7459
2.500 0.7716 0.00996 0.00341 -0.0990 0.3778 0.7488
2.750 0.7981 0.01031 0.00362 -0.0988 0.3423 0.7518
3.000 0.8242 0.01072 0.00386 -0.0986 0.3049 0.7550
3.250 0.8504 0.01113 0.00410 -0.0985 0.2717 0.7584
3.500 0.8771 0.01149 0.00434 -0.0984 0.2465 0.7622
3.750 0.9036 0.01182 0.00459 -0.0983 0.2260 0.7655
4.000 0.9300 0.01213 0.00484 -0.0981 0.2085 0.7687
4.250 0.9564 0.01245 0.00510 -0.0980 0.1927 0.7720
4.500 0.9829 0.01277 0.00537 -0.0979 0.1777 0.7755
4.750 1.0092 0.01310 0.00564 -0.0977 0.1642 0.7793
5.000 1.0352 0.01342 0.00592 -0.0975 0.1526 0.7825
5.250 1.0612 0.01371 0.00622 -0.0972 0.1438 0.7858
5.500 1.0868 0.01406 0.00653 -0.0969 0.1355 0.7893
5.750 1.1128 0.01436 0.00683 -0.0967 0.1286 0.7931
6.000 1.1381 0.01473 0.00718 -0.0964 0.1219 0.7971
6.250 1.1636 0.01500 0.00750 -0.0961 0.1174 0.8005
6.500 1.1885 0.01534 0.00785 -0.0956 0.1125 0.8043
6.750 1.2131 0.01572 0.00823 -0.0952 0.1075 0.8083
7.000 1.2382 0.01605 0.00858 -0.0949 0.1021 0.8123
7.250 1.2615 0.01647 0.00898 -0.0942 0.0958 0.8158
7.500 1.2855 0.01680 0.00936 -0.0937 0.0917 0.8198
7.750 1.3092 0.01718 0.00977 -0.0931 0.0877 0.8243
8.000 1.3322 0.01763 0.01020 -0.0924 0.0839 0.8288
8.250 1.3550 0.01800 0.01063 -0.0917 0.0810 0.8324
8.500 1.3774 0.01839 0.01108 -0.0909 0.0775 0.8365
8.750 1.3990 0.01885 0.01156 -0.0900 0.0743 0.8412
9.000 1.4200 0.01934 0.01207 -0.0891 0.0713 0.8458
9.250 1.4409 0.01975 0.01255 -0.0880 0.0688 0.8501
9.500 1.4608 0.02023 0.01308 -0.0869 0.0656 0.8548
9.750 1.4796 0.02080 0.01366 -0.0856 0.0624 0.8597
10.000 1.4975 0.02130 0.01423 -0.0842 0.0599 0.8639
10.250 1.5143 0.02182 0.01481 -0.0825 0.0570 0.8689
10.500 1.5272 0.02244 0.01547 -0.0803 0.0538 0.8744
10.750 1.5409 0.02309 0.01619 -0.0782 0.0508 0.8795
11.000 1.5548 0.02378 0.01694 -0.0763 0.0467 0.8856
11.250 1.5672 0.02462 0.01780 -0.0744 0.0423 0.8919
11.750 1.5880 0.02660 0.01986 -0.0703 0.0340 0.9059
12.250 1.6050 0.02891 0.02230 -0.0662 0.0295 0.9238
12.500 1.6115 0.03017 0.02364 -0.0641 0.0279 0.9380
13.000 1.6224 0.03306 0.02669 -0.0603 0.0257 1.0000
13.250 1.6309 0.03463 0.02835 -0.0592 0.0248 1.0000
13.500 1.6379 0.03637 0.03018 -0.0581 0.0240 1.0000
13.750 1.6432 0.03831 0.03220 -0.0570 0.0231 1.0000
14.000 1.6469 0.04047 0.03444 -0.0561 0.0225 1.0000
14.250 1.6484 0.04292 0.03698 -0.0552 0.0219 1.0000
14.500 1.6506 0.04535 0.03951 -0.0546 0.0214 1.0000
14.750 1.6536 0.04775 0.04203 -0.0541 0.0209 1.0000
15.000 1.6551 0.05040 0.04479 -0.0537 0.0205 1.0000
15.250 1.6549 0.05332 0.04782 -0.0535 0.0200 1.0000
15.500 1.6529 0.05652 0.05114 -0.0535 0.0196 1.0000
15.750 1.6496 0.06002 0.05476 -0.0537 0.0193 1.0000
16.000 1.6446 0.06388 0.05873 -0.0541 0.0189 1.0000
16.250 1.6375 0.06815 0.06312 -0.0549 0.0186 1.0000
16.500 1.6286 0.07282 0.06791 -0.0560 0.0183 1.0000
16.750 1.6171 0.07804 0.07325 -0.0574 0.0180 1.0000
17.000 1.6032 0.08381 0.07915 -0.0593 0.0178 1.0000
17.250 1.5913 0.08938 0.08486 -0.0612 0.0176 1.0000
17.500 1.5783 0.09526 0.09089 -0.0634 0.0174 1.0000
17.750 1.5637 0.10153 0.09730 -0.0659 0.0173 1.0000
18.000 1.5473 0.10824 0.10416 -0.0688 0.0172 1.0000
18.250 1.5292 0.11533 0.11141 -0.0720 0.0170 1.0000
18.500 1.5109 0.12266 0.11888 -0.0755 0.0169 1.0000
18.750 1.4925 0.13013 0.12649 -0.0793 0.0168 1.0000
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Polar data table (+)
Polar graphs
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