NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Reynolds number: 100,000 Max Cl/Cd: 30.72 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls421-il-100000-n5.txt Download as CSV file: xf-ls421-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6408 0.10208 0.09533 -0.0804 1.0000 0.0490
-16.500 -0.7002 0.08850 0.08134 -0.0882 1.0000 0.0489
-16.250 -0.7307 0.08089 0.07345 -0.0920 1.0000 0.0492
-16.000 -0.7535 0.07510 0.06740 -0.0944 1.0000 0.0495
-15.750 -0.7731 0.07041 0.06247 -0.0956 1.0000 0.0500
-15.500 -0.7899 0.06695 0.05881 -0.0955 1.0000 0.0504
-15.250 -0.7975 0.06554 0.05742 -0.0936 1.0000 0.0508
-15.000 -0.7937 0.06350 0.05535 -0.0941 0.9959 0.0515
-14.750 -0.7830 0.06087 0.05261 -0.0964 0.9909 0.0524
-14.500 -0.7736 0.05822 0.04981 -0.0982 0.9846 0.0533
-14.250 -0.7628 0.05557 0.04695 -0.1002 0.9796 0.0544
-14.000 -0.7521 0.05306 0.04419 -0.1016 0.9737 0.0555
-13.750 -0.7341 0.05136 0.04246 -0.1029 0.9682 0.0566
-13.500 -0.7157 0.04972 0.04078 -0.1044 0.9639 0.0578
-13.250 -0.7009 0.04811 0.03907 -0.1052 0.9579 0.0593
-13.000 -0.6854 0.04648 0.03726 -0.1059 0.9522 0.0611
-12.750 -0.6659 0.04510 0.03584 -0.1068 0.9477 0.0626
-12.500 -0.6494 0.04389 0.03462 -0.1070 0.9419 0.0642
-12.250 -0.6331 0.04271 0.03335 -0.1071 0.9357 0.0661
-12.000 -0.6148 0.04152 0.03203 -0.1073 0.9308 0.0683
-11.750 -0.5988 0.04046 0.03101 -0.1072 0.9258 0.0702
-11.500 -0.5847 0.03951 0.03001 -0.1067 0.9198 0.0726
-11.250 -0.5679 0.03857 0.02898 -0.1063 0.9149 0.0753
-11.000 -0.5521 0.03756 0.02801 -0.1060 0.9108 0.0777
-10.750 -0.5373 0.03670 0.02709 -0.1054 0.9061 0.0809
-10.500 -0.5244 0.03586 0.02625 -0.1045 0.9003 0.0841
-10.250 -0.5103 0.03499 0.02537 -0.1038 0.8953 0.0879
-10.000 -0.4949 0.03410 0.02446 -0.1031 0.8913 0.0922
-9.750 -0.4807 0.03325 0.02360 -0.1024 0.8874 0.0972
-9.500 -0.4701 0.03254 0.02293 -0.1011 0.8820 0.1025
-9.250 -0.4573 0.03186 0.02223 -0.1000 0.8773 0.1094
-9.000 -0.4456 0.03105 0.02147 -0.0988 0.8732 0.1168
-8.750 -0.4322 0.03025 0.02070 -0.0977 0.8697 0.1262
-8.500 -0.4214 0.02958 0.02007 -0.0962 0.8656 0.1370
-8.250 -0.4164 0.02914 0.01968 -0.0937 0.8595 0.1479
-8.000 -0.4097 0.02862 0.01922 -0.0914 0.8548 0.1612
-7.750 -0.3987 0.02799 0.01867 -0.0899 0.8512 0.1785
-7.500 -0.3849 0.02732 0.01809 -0.0888 0.8483 0.2001
-7.250 -0.3715 0.02667 0.01757 -0.0877 0.8454 0.2254
-7.000 -0.3683 0.02640 0.01746 -0.0850 0.8388 0.2500
-6.750 -0.3567 0.02590 0.01713 -0.0835 0.8342 0.2834
-6.500 -0.3406 0.02534 0.01676 -0.0826 0.8309 0.3236
-6.250 -0.3214 0.02479 0.01645 -0.0821 0.8283 0.3701
-6.000 -0.2990 0.02441 0.01635 -0.0817 0.8263 0.4215
-5.750 -0.2734 0.02450 0.01674 -0.0808 0.8247 0.4699
-5.500 -0.2663 0.02523 0.01765 -0.0772 0.8178 0.5008
-5.250 -0.2459 0.02592 0.01844 -0.0752 0.8137 0.5278
-5.000 -0.2218 0.02636 0.01887 -0.0743 0.8108 0.5520
-4.750 -0.1953 0.02662 0.01906 -0.0742 0.8084 0.5739
-4.500 -0.1667 0.02698 0.01935 -0.0740 0.8063 0.5908
-4.250 -0.1367 0.02731 0.01960 -0.0741 0.8046 0.6052
-4.000 -0.1173 0.02766 0.01988 -0.0733 0.8004 0.6199
-3.750 -0.1095 0.02871 0.02095 -0.0696 0.7941 0.6273
-3.500 -0.0866 0.02900 0.02116 -0.0693 0.7905 0.6403
-3.250 -0.0621 0.02970 0.02183 -0.0675 0.7877 0.6470
-3.000 -0.0317 0.02969 0.02172 -0.0686 0.7855 0.6598
-2.750 -0.0042 0.03017 0.02218 -0.0674 0.7838 0.6640
-2.500 0.0256 0.03039 0.02235 -0.0672 0.7824 0.6697
-2.250 0.0201 0.03108 0.02302 -0.0640 0.7719 0.6804
-2.000 0.0405 0.03153 0.02346 -0.0622 0.7684 0.6837
-1.750 0.0663 0.03177 0.02367 -0.0614 0.7658 0.6880
-1.500 0.0972 0.03175 0.02360 -0.0619 0.7638 0.6941
-1.250 0.1333 0.03146 0.02322 -0.0642 0.7623 0.7022
-1.000 0.1184 0.03279 0.02463 -0.0576 0.7512 0.7057
-0.750 0.1406 0.03304 0.02486 -0.0563 0.7473 0.7101
-0.500 0.1709 0.03302 0.02481 -0.0568 0.7448 0.7158
-0.250 0.2109 0.03267 0.02438 -0.0599 0.7430 0.7232
0.000 0.2423 0.03255 0.02426 -0.0598 0.7414 0.7258
0.500 0.2539 0.03380 0.02557 -0.0535 0.7251 0.7332
0.750 0.2895 0.03350 0.02524 -0.0548 0.7229 0.7373
1.000 0.3307 0.03303 0.02474 -0.0575 0.7214 0.7418
1.250 0.3735 0.03251 0.02418 -0.0602 0.7201 0.7454
1.750 0.3899 0.03351 0.02527 -0.0546 0.7026 0.7508
2.000 0.4287 0.03287 0.02462 -0.0558 0.7009 0.7535
2.500 0.4644 0.03342 0.02523 -0.0541 0.6838 0.7601
2.750 0.5076 0.03252 0.02431 -0.0564 0.6818 0.7634
3.000 0.5549 0.03153 0.02331 -0.0594 0.6800 0.7662
3.500 0.5869 0.03184 0.02372 -0.0560 0.6620 0.7701
4.000 0.6297 0.03173 0.02370 -0.0542 0.6436 0.7755
4.500 0.6824 0.03120 0.02323 -0.0540 0.6238 0.7808
4.750 0.6969 0.03188 0.02397 -0.0533 0.6084 0.7837
5.000 0.7221 0.03200 0.02411 -0.0538 0.5953 0.7865
5.250 0.7517 0.03129 0.02343 -0.0533 0.5855 0.7884
5.500 0.7670 0.03168 0.02387 -0.0518 0.5690 0.7908
5.750 0.7887 0.03169 0.02391 -0.0509 0.5527 0.7932
6.000 0.8158 0.03139 0.02359 -0.0507 0.5352 0.7955
6.250 0.8467 0.03087 0.02302 -0.0508 0.5152 0.7979
6.500 0.8798 0.03027 0.02228 -0.0512 0.4911 0.8003
6.750 0.9077 0.03016 0.02201 -0.0512 0.4632 0.8028
7.000 0.9326 0.03036 0.02201 -0.0511 0.4331 0.8056
7.250 0.9490 0.03090 0.02239 -0.0498 0.4052 0.8079
7.500 0.9615 0.03166 0.02303 -0.0480 0.3789 0.8104
7.750 0.9734 0.03256 0.02380 -0.0465 0.3544 0.8130
8.000 0.9854 0.03357 0.02467 -0.0451 0.3317 0.8156
8.250 0.9979 0.03465 0.02563 -0.0441 0.3108 0.8182
8.500 1.0110 0.03578 0.02666 -0.0432 0.2916 0.8209
8.750 1.0247 0.03696 0.02776 -0.0426 0.2740 0.8236
9.000 1.0383 0.03812 0.02886 -0.0419 0.2581 0.8260
9.250 1.0496 0.03921 0.02993 -0.0407 0.2446 0.8282
9.500 1.0607 0.04037 0.03104 -0.0394 0.2326 0.8309
9.750 1.0722 0.04157 0.03220 -0.0384 0.2215 0.8339
10.000 1.0859 0.04273 0.03336 -0.0377 0.2114 0.8371
10.250 1.0982 0.04405 0.03461 -0.0371 0.2028 0.8404
10.500 1.1140 0.04526 0.03586 -0.0369 0.1940 0.8435
10.750 1.1240 0.04655 0.03709 -0.0358 0.1873 0.8459
11.000 1.1375 0.04768 0.03830 -0.0350 0.1803 0.8486
11.250 1.1489 0.04902 0.03962 -0.0342 0.1743 0.8515
11.500 1.1622 0.05029 0.04091 -0.0337 0.1687 0.8547
11.750 1.1757 0.05164 0.04232 -0.0333 0.1631 0.8579
12.250 1.1999 0.05437 0.04509 -0.0321 0.1538 0.8645
12.500 1.2109 0.05576 0.04655 -0.0313 0.1493 0.8682
12.750 1.2222 0.05719 0.04795 -0.0308 0.1457 0.8722
13.000 1.2349 0.05869 0.04953 -0.0304 0.1417 0.8762
13.250 1.2458 0.06023 0.05116 -0.0299 0.1379 0.8798
13.500 1.2553 0.06176 0.05272 -0.0293 0.1347 0.8836
13.750 1.2666 0.06323 0.05419 -0.0287 0.1317 0.8876
14.000 1.2766 0.06501 0.05613 -0.0285 0.1284 0.8918
14.250 1.2857 0.06676 0.05796 -0.0280 0.1254 0.8960
14.500 1.2942 0.06838 0.05962 -0.0274 0.1228 0.9006
14.750 1.3040 0.07004 0.06130 -0.0270 0.1204 0.9060
15.000 1.3103 0.07212 0.06357 -0.0266 0.1177 0.9115
15.250 1.3159 0.07408 0.06565 -0.0260 0.1152 0.9180
15.750 1.3306 0.07756 0.06919 -0.0251 0.1111 0.9339
16.000 1.3330 0.07991 0.07173 -0.0247 0.1091 0.9446
16.250 1.3331 0.08242 0.07443 -0.0244 0.1070 0.9631
16.500 1.3357 0.08487 0.07701 -0.0248 0.1050 1.0000
16.750 1.3434 0.08740 0.07959 -0.0257 0.1031 1.0000
17.000 1.3549 0.08939 0.08155 -0.0264 0.1014 1.0000
17.250 1.3540 0.09309 0.08546 -0.0276 0.0996 1.0000
17.500 1.3509 0.09718 0.08976 -0.0289 0.0978 1.0000
17.750 1.3498 0.10100 0.09374 -0.0304 0.0961 1.0000
18.000 1.3518 0.10437 0.09720 -0.0318 0.0945 1.0000
18.250 1.3591 0.10690 0.09974 -0.0329 0.0931 1.0000
18.500 1.3633 0.10991 0.10280 -0.0343 0.0917 1.0000
18.750 1.3434 0.11684 0.11007 -0.0375 0.0903 1.0000
19.000 1.3232 0.12410 0.11761 -0.0413 0.0888 1.0000
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Polar data table (+)
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