NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.54 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413mod-il-1000000-n5.txt Download as CSV file: xf-ls413mod-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.0347 0.06047 0.05757 -0.0561 1.0000 0.0116
-16.000 -1.0547 0.05324 0.05015 -0.0612 1.0000 0.0116
-15.750 -1.0665 0.04796 0.04472 -0.0646 1.0000 0.0117
-15.500 -1.0731 0.04382 0.04044 -0.0670 1.0000 0.0117
-15.250 -1.0760 0.04043 0.03693 -0.0686 1.0000 0.0118
-15.000 -1.0756 0.03763 0.03401 -0.0696 1.0000 0.0118
-14.750 -1.0736 0.03514 0.03141 -0.0703 1.0000 0.0119
-14.500 -1.0695 0.03300 0.02916 -0.0706 1.0000 0.0119
-14.250 -1.0641 0.03113 0.02719 -0.0706 1.0000 0.0120
-14.000 -1.0587 0.02944 0.02540 -0.0701 1.0000 0.0121
-13.750 -1.0539 0.02802 0.02389 -0.0690 1.0000 0.0122
-13.500 -1.0463 0.02672 0.02250 -0.0681 1.0000 0.0122
-13.250 -1.0345 0.02552 0.02121 -0.0676 1.0000 0.0123
-13.000 -1.0212 0.02454 0.02014 -0.0668 1.0000 0.0124
-12.750 -1.0069 0.02366 0.01918 -0.0657 1.0000 0.0125
-12.500 -0.9848 0.02283 0.01826 -0.0660 0.9990 0.0127
-12.250 -0.9568 0.02192 0.01727 -0.0673 0.9968 0.0128
-12.000 -0.9278 0.02112 0.01638 -0.0687 0.9946 0.0130
-11.750 -0.8988 0.02038 0.01557 -0.0700 0.9925 0.0131
-11.500 -0.8700 0.01979 0.01491 -0.0710 0.9894 0.0132
-11.250 -0.8418 0.01874 0.01377 -0.0723 0.9858 0.0134
-11.000 -0.8116 0.01781 0.01278 -0.0739 0.9826 0.0136
-10.750 -0.7831 0.01713 0.01205 -0.0748 0.9766 0.0138
-10.500 -0.7527 0.01649 0.01136 -0.0760 0.9711 0.0140
-10.250 -0.7239 0.01591 0.01073 -0.0769 0.9646 0.0141
-10.000 -0.6949 0.01536 0.01012 -0.0776 0.9574 0.0142
-9.750 -0.6668 0.01486 0.00958 -0.0781 0.9489 0.0144
-9.500 -0.6391 0.01438 0.00904 -0.0785 0.9395 0.0145
-9.250 -0.6117 0.01394 0.00854 -0.0787 0.9287 0.0147
-9.000 -0.5843 0.01352 0.00805 -0.0790 0.9189 0.0148
-8.750 -0.5567 0.01313 0.00759 -0.0792 0.9091 0.0150
-8.500 -0.5287 0.01274 0.00715 -0.0795 0.8995 0.0152
-8.250 -0.5007 0.01238 0.00672 -0.0798 0.8901 0.0154
-8.000 -0.4723 0.01204 0.00632 -0.0801 0.8803 0.0156
-7.750 -0.4436 0.01173 0.00594 -0.0805 0.8716 0.0158
-7.500 -0.4148 0.01143 0.00559 -0.0809 0.8624 0.0160
-7.250 -0.3857 0.01115 0.00525 -0.0813 0.8541 0.0162
-7.000 -0.3565 0.01090 0.00495 -0.0817 0.8454 0.0164
-6.750 -0.3270 0.01056 0.00457 -0.0823 0.8375 0.0168
-6.500 -0.2974 0.01030 0.00427 -0.0828 0.8292 0.0173
-6.250 -0.2677 0.01008 0.00403 -0.0833 0.8214 0.0178
-6.000 -0.2380 0.00990 0.00381 -0.0838 0.8131 0.0184
-5.750 -0.2081 0.00973 0.00361 -0.0843 0.8054 0.0190
-5.500 -0.1782 0.00956 0.00340 -0.0848 0.7970 0.0196
-5.250 -0.1483 0.00941 0.00322 -0.0853 0.7888 0.0201
-5.000 -0.1180 0.00921 0.00298 -0.0858 0.7794 0.0212
-4.750 -0.0879 0.00906 0.00281 -0.0864 0.7698 0.0222
-4.500 -0.0579 0.00895 0.00265 -0.0868 0.7597 0.0235
-4.250 -0.0277 0.00884 0.00251 -0.0874 0.7505 0.0246
-4.000 0.0027 0.00871 0.00236 -0.0879 0.7428 0.0269
-3.750 0.0331 0.00858 0.00223 -0.0885 0.7353 0.0299
-3.500 0.0639 0.00840 0.00211 -0.0892 0.7282 0.0441
-3.250 0.0948 0.00825 0.00200 -0.0900 0.7210 0.0617
-3.000 0.1258 0.00807 0.00190 -0.0908 0.7128 0.0878
-2.750 0.1571 0.00786 0.00181 -0.0917 0.7053 0.1261
-2.500 0.1891 0.00759 0.00171 -0.0928 0.6972 0.1849
-2.250 0.2217 0.00727 0.00162 -0.0941 0.6885 0.2621
-2.000 0.2555 0.00685 0.00153 -0.0959 0.6760 0.3793
-1.750 0.2880 0.00660 0.00147 -0.0972 0.6589 0.4598
-1.500 0.3204 0.00640 0.00145 -0.0984 0.6414 0.5402
-1.250 0.3517 0.00632 0.00148 -0.0992 0.6275 0.5965
-1.000 0.3821 0.00633 0.00154 -0.0997 0.6144 0.6341
-0.750 0.4118 0.00641 0.00158 -0.1000 0.5991 0.6498
-0.500 0.4412 0.00652 0.00162 -0.1003 0.5787 0.6594
-0.250 0.4703 0.00667 0.00167 -0.1005 0.5502 0.6694
0.000 0.4991 0.00686 0.00174 -0.1007 0.5203 0.6784
0.250 0.5280 0.00704 0.00181 -0.1009 0.4940 0.6829
0.500 0.5567 0.00723 0.00189 -0.1011 0.4681 0.6862
0.750 0.5856 0.00739 0.00197 -0.1014 0.4471 0.6896
1.000 0.6143 0.00758 0.00206 -0.1016 0.4233 0.6934
1.250 0.6427 0.00781 0.00216 -0.1017 0.3973 0.6972
1.500 0.6712 0.00801 0.00228 -0.1019 0.3733 0.7016
1.750 0.6993 0.00826 0.00242 -0.1020 0.3446 0.7064
2.000 0.7266 0.00862 0.00259 -0.1020 0.3054 0.7108
2.250 0.7539 0.00897 0.00277 -0.1020 0.2699 0.7140
2.500 0.7814 0.00927 0.00295 -0.1021 0.2431 0.7167
2.750 0.8093 0.00950 0.00311 -0.1022 0.2247 0.7193
3.000 0.8371 0.00973 0.00327 -0.1022 0.2084 0.7221
3.250 0.8649 0.00997 0.00344 -0.1023 0.1936 0.7252
3.500 0.8926 0.01021 0.00362 -0.1023 0.1788 0.7283
3.750 0.9201 0.01047 0.00381 -0.1023 0.1645 0.7310
4.250 0.9749 0.01093 0.00421 -0.1023 0.1427 0.7376
4.500 1.0022 0.01117 0.00441 -0.1023 0.1341 0.7414
4.750 1.0294 0.01142 0.00462 -0.1023 0.1265 0.7447
5.000 1.0566 0.01165 0.00483 -0.1022 0.1203 0.7476
5.250 1.0838 0.01186 0.00506 -0.1022 0.1154 0.7510
5.500 1.1105 0.01211 0.00530 -0.1020 0.1098 0.7546
5.750 1.1375 0.01233 0.00553 -0.1019 0.1061 0.7584
6.000 1.1642 0.01258 0.00577 -0.1018 0.1012 0.7618
6.250 1.1901 0.01289 0.00605 -0.1016 0.0942 0.7651
6.500 1.2162 0.01316 0.00632 -0.1014 0.0887 0.7687
6.750 1.2417 0.01348 0.00662 -0.1011 0.0829 0.7729
7.000 1.2678 0.01373 0.00689 -0.1008 0.0804 0.7772
7.250 1.2934 0.01401 0.00718 -0.1006 0.0773 0.7809
7.500 1.3184 0.01434 0.00751 -0.1002 0.0737 0.7847
7.750 1.3435 0.01464 0.00783 -0.0998 0.0707 0.7888
8.000 1.3683 0.01495 0.00815 -0.0994 0.0675 0.7931
8.250 1.3924 0.01532 0.00852 -0.0989 0.0640 0.7971
8.500 1.4162 0.01567 0.00889 -0.0983 0.0611 0.8013
8.750 1.4403 0.01599 0.00925 -0.0978 0.0592 0.8057
9.000 1.4637 0.01635 0.00963 -0.0971 0.0565 0.8100
9.250 1.4859 0.01679 0.01007 -0.0963 0.0531 0.8138
9.500 1.5085 0.01717 0.01048 -0.0956 0.0506 0.8178
9.750 1.5299 0.01762 0.01095 -0.0947 0.0463 0.8224
10.000 1.5498 0.01816 0.01147 -0.0935 0.0408 0.8269
10.250 1.5671 0.01886 0.01213 -0.0920 0.0335 0.8310
10.500 1.5839 0.01953 0.01281 -0.0904 0.0292 0.8353
10.750 1.5992 0.02023 0.01352 -0.0885 0.0263 0.8399
11.000 1.6146 0.02084 0.01416 -0.0867 0.0245 0.8442
11.250 1.6255 0.02150 0.01487 -0.0840 0.0230 0.8485
11.500 1.6374 0.02226 0.01568 -0.0817 0.0217 0.8533
11.750 1.6512 0.02295 0.01643 -0.0798 0.0210 0.8581
12.000 1.6642 0.02371 0.01725 -0.0779 0.0203 0.8626
12.250 1.6764 0.02455 0.01816 -0.0760 0.0196 0.8679
12.500 1.6878 0.02548 0.01915 -0.0741 0.0190 0.8733
12.750 1.6983 0.02651 0.02025 -0.0722 0.0184 0.8784
13.000 1.7078 0.02764 0.02145 -0.0704 0.0177 0.8840
13.250 1.7188 0.02870 0.02259 -0.0688 0.0173 0.8898
13.500 1.7287 0.02986 0.02384 -0.0673 0.0169 0.8960
13.750 1.7376 0.03114 0.02520 -0.0658 0.0164 0.9033
14.000 1.7454 0.03253 0.02668 -0.0642 0.0160 0.9115
14.250 1.7521 0.03406 0.02829 -0.0628 0.0156 0.9219
14.500 1.7570 0.03566 0.03000 -0.0612 0.0152 0.9386
14.750 1.7587 0.03741 0.03185 -0.0594 0.0149 1.0000
15.000 1.7625 0.03949 0.03400 -0.0584 0.0145 1.0000
15.250 1.7678 0.04148 0.03608 -0.0576 0.0142 1.0000
15.500 1.7722 0.04360 0.03828 -0.0568 0.0140 1.0000
15.750 1.7751 0.04592 0.04068 -0.0562 0.0138 1.0000
16.000 1.7767 0.04844 0.04330 -0.0557 0.0135 1.0000
16.250 1.7771 0.05120 0.04614 -0.0554 0.0132 1.0000
16.500 1.7763 0.05416 0.04919 -0.0552 0.0130 1.0000
16.750 1.7740 0.05740 0.05252 -0.0552 0.0127 1.0000
17.000 1.7702 0.06095 0.05618 -0.0554 0.0125 1.0000
17.250 1.7650 0.06480 0.06013 -0.0559 0.0122 1.0000
17.500 1.7576 0.06904 0.06447 -0.0566 0.0120 1.0000
17.750 1.7483 0.07368 0.06921 -0.0576 0.0118 1.0000
18.000 1.7369 0.07878 0.07443 -0.0589 0.0116 1.0000
18.250 1.7255 0.08400 0.07977 -0.0604 0.0115 1.0000
18.500 1.7124 0.08957 0.08547 -0.0622 0.0114 1.0000
18.750 1.6974 0.09557 0.09161 -0.0644 0.0113 1.0000
19.000 1.6800 0.10209 0.09826 -0.0669 0.0112 1.0000
19.250 1.6598 0.10921 0.10552 -0.0699 0.0111 1.0000
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Polar data table (+)
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