NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 500,000 Max Cl/Cd: 96.18 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413-il-500000.txt Download as CSV file: xf-ls413-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3482 0.11359 0.11122 -0.0497 1.0000 0.0348
-12.500 -0.3594 0.10794 0.10559 -0.0520 1.0000 0.0350
-12.250 -0.3695 0.10254 0.10021 -0.0536 1.0000 0.0351
-12.000 -0.3789 0.09787 0.09557 -0.0529 1.0000 0.0355
-11.750 -0.3848 0.09566 0.09340 -0.0512 1.0000 0.0357
-11.500 -0.3915 0.09314 0.09091 -0.0499 0.9997 0.0359
-11.250 -0.3854 0.08898 0.08675 -0.0521 0.9985 0.0362
-11.000 -0.3820 0.08415 0.08192 -0.0549 0.9972 0.0366
-10.750 -0.3819 0.07834 0.07611 -0.0584 0.9957 0.0370
-10.500 -0.3882 0.07066 0.06843 -0.0634 0.9943 0.0374
-10.250 -0.4572 0.05077 0.04837 -0.0792 0.9905 0.0373
-10.000 -0.4833 0.04319 0.04060 -0.0859 0.9850 0.0374
-9.750 -0.4905 0.03805 0.03526 -0.0909 0.9787 0.0377
-9.500 -0.4860 0.03363 0.03063 -0.0940 0.9731 0.0384
-9.250 -0.4761 0.02946 0.02618 -0.0965 0.9687 0.0398
-9.000 -0.5268 0.02857 0.02363 -0.0979 0.9688 0.0286
-8.750 -0.5054 0.02559 0.02038 -0.0983 0.9626 0.0278
-8.500 -0.4787 0.02307 0.01756 -0.0993 0.9587 0.0274
-8.250 -0.4505 0.02116 0.01542 -0.1000 0.9555 0.0272
-8.000 -0.4258 0.01982 0.01391 -0.0999 0.9496 0.0273
-7.750 -0.3989 0.01865 0.01259 -0.1000 0.9450 0.0275
-7.500 -0.3715 0.01765 0.01148 -0.1002 0.9412 0.0278
-7.250 -0.3454 0.01682 0.01057 -0.1001 0.9360 0.0281
-7.000 -0.3188 0.01608 0.00975 -0.1000 0.9308 0.0285
-6.750 -0.2916 0.01545 0.00905 -0.1000 0.9266 0.0290
-6.500 -0.2644 0.01487 0.00840 -0.1001 0.9219 0.0294
-6.250 -0.2384 0.01389 0.00744 -0.1002 0.9167 0.0305
-6.000 -0.2104 0.01343 0.00698 -0.1005 0.9124 0.0317
-5.750 -0.1819 0.01301 0.00653 -0.1009 0.9087 0.0330
-5.500 -0.1533 0.01261 0.00610 -0.1013 0.9041 0.0343
-5.250 -0.1241 0.01204 0.00550 -0.1020 0.8997 0.0361
-5.000 -0.0946 0.01161 0.00508 -0.1026 0.8959 0.0386
-4.750 -0.0649 0.01134 0.00476 -0.1031 0.8925 0.0417
-4.500 -0.0346 0.01091 0.00436 -0.1040 0.8884 0.0472
-4.250 -0.0043 0.01057 0.00405 -0.1048 0.8843 0.0556
-4.000 0.0266 0.01018 0.00374 -0.1057 0.8806 0.0778
-3.750 0.0610 0.00901 0.00333 -0.1084 0.8775 0.2679
-3.500 0.0967 0.00799 0.00307 -0.1113 0.8739 0.4695
-3.250 0.1287 0.00766 0.00315 -0.1124 0.8696 0.5924
-3.000 0.1586 0.00769 0.00321 -0.1128 0.8656 0.6269
-2.750 0.1885 0.00775 0.00324 -0.1130 0.8622 0.6469
-2.500 0.2182 0.00785 0.00331 -0.1133 0.8589 0.6636
-2.250 0.2475 0.00796 0.00343 -0.1135 0.8547 0.6796
-2.000 0.2761 0.00809 0.00359 -0.1133 0.8504 0.6953
-1.750 0.3038 0.00823 0.00376 -0.1129 0.8465 0.7078
-1.500 0.3332 0.00831 0.00379 -0.1131 0.8424 0.7146
-1.250 0.3618 0.00831 0.00380 -0.1132 0.8366 0.7182
-1.000 0.3908 0.00830 0.00375 -0.1132 0.8306 0.7220
-0.750 0.4202 0.00834 0.00374 -0.1134 0.8244 0.7267
-0.500 0.4494 0.00833 0.00371 -0.1136 0.8177 0.7308
-0.250 0.4779 0.00834 0.00369 -0.1135 0.8114 0.7341
0.000 0.5063 0.00833 0.00370 -0.1134 0.8028 0.7381
0.250 0.5355 0.00835 0.00367 -0.1136 0.7957 0.7430
0.500 0.5640 0.00833 0.00366 -0.1135 0.7856 0.7475
0.750 0.5916 0.00833 0.00365 -0.1132 0.7753 0.7512
1.000 0.6202 0.00833 0.00364 -0.1132 0.7659 0.7548
1.250 0.6494 0.00834 0.00365 -0.1135 0.7569 0.7579
1.500 0.6789 0.00837 0.00364 -0.1138 0.7481 0.7607
1.750 0.7076 0.00836 0.00365 -0.1139 0.7367 0.7634
2.000 0.7357 0.00838 0.00368 -0.1138 0.7239 0.7658
2.250 0.7637 0.00841 0.00370 -0.1138 0.7093 0.7683
2.500 0.7915 0.00847 0.00373 -0.1137 0.6891 0.7711
2.750 0.8189 0.00858 0.00377 -0.1135 0.6633 0.7743
3.000 0.8454 0.00879 0.00383 -0.1132 0.6238 0.7774
3.250 0.8669 0.00930 0.00398 -0.1119 0.5449 0.7799
3.500 0.8846 0.01019 0.00438 -0.1102 0.4453 0.7826
3.750 0.9040 0.01100 0.00482 -0.1088 0.3679 0.7857
4.000 0.9246 0.01175 0.00522 -0.1078 0.3001 0.7889
4.250 0.9469 0.01238 0.00560 -0.1070 0.2510 0.7922
4.500 0.9693 0.01296 0.00596 -0.1063 0.2087 0.7953
4.750 0.9917 0.01346 0.00632 -0.1054 0.1795 0.7982
5.000 1.0146 0.01392 0.00668 -0.1047 0.1590 0.8014
5.250 1.0380 0.01436 0.00705 -0.1041 0.1430 0.8048
5.500 1.0621 0.01475 0.00740 -0.1035 0.1306 0.8084
5.750 1.0855 0.01515 0.00776 -0.1029 0.1208 0.8116
6.000 1.1077 0.01558 0.00815 -0.1020 0.1123 0.8150
6.250 1.1309 0.01594 0.00855 -0.1012 0.1064 0.8189
6.500 1.1535 0.01638 0.00896 -0.1004 0.1004 0.8230
6.750 1.1752 0.01685 0.00945 -0.0995 0.0952 0.8268
7.000 1.1977 0.01718 0.00983 -0.0986 0.0911 0.8305
7.250 1.2181 0.01767 0.01032 -0.0975 0.0864 0.8347
7.500 1.2385 0.01818 0.01085 -0.0963 0.0825 0.8394
7.750 1.2604 0.01852 0.01125 -0.0954 0.0792 0.8437
8.000 1.2797 0.01897 0.01172 -0.0941 0.0757 0.8482
8.250 1.2942 0.01971 0.01248 -0.0919 0.0719 0.8538
8.500 1.3132 0.02002 0.01287 -0.0904 0.0697 0.8592
8.750 1.3309 0.02041 0.01333 -0.0888 0.0669 0.8648
9.000 1.3480 0.02099 0.01393 -0.0872 0.0641 0.8710
9.250 1.3601 0.02187 0.01485 -0.0849 0.0611 0.8771
9.500 1.3791 0.02231 0.01538 -0.0836 0.0592 0.8840
9.750 1.3964 0.02283 0.01598 -0.0821 0.0569 0.8911
10.000 1.4119 0.02347 0.01666 -0.0804 0.0546 0.8995
10.250 1.4202 0.02461 0.01784 -0.0778 0.0519 0.9092
10.500 1.4368 0.02508 0.01843 -0.0762 0.0504 0.9215
10.750 1.4494 0.02562 0.01908 -0.0740 0.0486 0.9442
11.000 1.4618 0.02628 0.01980 -0.0721 0.0468 1.0000
11.250 1.4750 0.02742 0.02095 -0.0707 0.0449 1.0000
11.500 1.4854 0.02879 0.02238 -0.0690 0.0433 1.0000
11.750 1.5011 0.02972 0.02339 -0.0680 0.0420 1.0000
12.000 1.5150 0.03076 0.02451 -0.0667 0.0407 1.0000
12.250 1.5277 0.03189 0.02568 -0.0655 0.0395 1.0000
12.500 1.5379 0.03323 0.02707 -0.0640 0.0383 1.0000
12.750 1.5420 0.03513 0.02901 -0.0620 0.0371 1.0000
13.000 1.5498 0.03675 0.03072 -0.0604 0.0363 1.0000
13.250 1.5604 0.03811 0.03220 -0.0592 0.0356 1.0000
13.500 1.5703 0.03954 0.03373 -0.0580 0.0346 1.0000
13.750 1.5788 0.04109 0.03535 -0.0569 0.0337 1.0000
14.000 1.5870 0.04269 0.03702 -0.0558 0.0329 1.0000
14.250 1.5921 0.04461 0.03900 -0.0546 0.0321 1.0000
14.500 1.5929 0.04700 0.04145 -0.0533 0.0314 1.0000
14.750 1.5892 0.04989 0.04443 -0.0517 0.0307 1.0000
15.000 1.5940 0.05201 0.04668 -0.0509 0.0303 1.0000
15.250 1.5977 0.05432 0.04913 -0.0502 0.0299 1.0000
15.500 1.6002 0.05682 0.05176 -0.0497 0.0293 1.0000
15.750 1.6012 0.05955 0.05460 -0.0493 0.0288 1.0000
16.000 1.6014 0.06247 0.05763 -0.0490 0.0283 1.0000
16.250 1.6006 0.06560 0.06088 -0.0490 0.0278 1.0000
16.500 1.5987 0.06899 0.06437 -0.0491 0.0275 1.0000
16.750 1.5953 0.07265 0.06814 -0.0495 0.0271 1.0000
17.000 1.5901 0.07667 0.07225 -0.0502 0.0268 1.0000
17.250 1.5830 0.08105 0.07673 -0.0510 0.0264 1.0000
17.500 1.5733 0.08587 0.08164 -0.0521 0.0260 1.0000
17.750 1.5592 0.09145 0.08736 -0.0535 0.0256 1.0000
18.000 1.5513 0.09657 0.09263 -0.0556 0.0254 1.0000
18.250 1.5415 0.10209 0.09832 -0.0580 0.0252 1.0000
18.500 1.5301 0.10808 0.10448 -0.0608 0.0250 1.0000
18.750 1.5173 0.11444 0.11100 -0.0640 0.0248 1.0000
19.000 1.5036 0.12109 0.11781 -0.0676 0.0246 1.0000
19.250 1.4888 0.12806 0.12493 -0.0715 0.0243 1.0000
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Polar data table (+)
Polar graphs
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