NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.37 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417mod-il-1000000-n5.txt Download as CSV file: xf-ls417mod-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0578 0.10687 0.10342 -0.0384 1.0000 0.0116
-19.500 -1.0839 0.09852 0.09494 -0.0429 1.0000 0.0116
-19.250 -1.1076 0.09073 0.08701 -0.0471 1.0000 0.0116
-19.000 -1.1279 0.08362 0.07975 -0.0509 1.0000 0.0117
-18.750 -1.1436 0.07740 0.07341 -0.0542 1.0000 0.0117
-18.500 -1.1568 0.07164 0.06754 -0.0572 1.0000 0.0117
-18.250 -1.1657 0.06668 0.06246 -0.0597 1.0000 0.0117
-18.000 -1.1727 0.06213 0.05780 -0.0619 1.0000 0.0118
-17.750 -1.1777 0.05798 0.05356 -0.0638 1.0000 0.0118
-17.500 -1.1837 0.05390 0.04937 -0.0655 1.0000 0.0119
-17.250 -1.1869 0.05033 0.04572 -0.0668 1.0000 0.0120
-17.000 -1.1872 0.04725 0.04255 -0.0677 1.0000 0.0121
-16.750 -1.1856 0.04454 0.03977 -0.0683 1.0000 0.0122
-16.500 -1.1819 0.04217 0.03734 -0.0687 1.0000 0.0123
-16.250 -1.1771 0.04002 0.03513 -0.0689 1.0000 0.0124
-16.000 -1.1713 0.03805 0.03311 -0.0690 1.0000 0.0125
-15.750 -1.1639 0.03630 0.03130 -0.0689 1.0000 0.0126
-15.500 -1.1556 0.03466 0.02961 -0.0687 1.0000 0.0128
-15.250 -1.1466 0.03313 0.02803 -0.0684 1.0000 0.0129
-15.000 -1.1366 0.03171 0.02657 -0.0681 1.0000 0.0130
-14.750 -1.1261 0.03038 0.02520 -0.0676 1.0000 0.0132
-14.500 -1.1149 0.02915 0.02393 -0.0671 1.0000 0.0133
-14.250 -1.1036 0.02797 0.02270 -0.0665 1.0000 0.0134
-14.000 -1.0919 0.02689 0.02158 -0.0657 1.0000 0.0136
-13.750 -1.0806 0.02586 0.02051 -0.0647 1.0000 0.0138
-13.500 -1.0696 0.02492 0.01953 -0.0635 1.0000 0.0139
-13.250 -1.0606 0.02403 0.01860 -0.0619 1.0000 0.0140
-13.000 -1.0533 0.02323 0.01778 -0.0597 1.0000 0.0142
-12.750 -1.0328 0.02235 0.01686 -0.0601 0.9972 0.0143
-12.250 -0.9855 0.02057 0.01501 -0.0618 0.9853 0.0147
-12.000 -0.9600 0.01972 0.01413 -0.0629 0.9774 0.0150
-11.750 -0.9320 0.01898 0.01338 -0.0643 0.9681 0.0153
-11.500 -0.9026 0.01832 0.01270 -0.0657 0.9574 0.0157
-11.250 -0.8743 0.01771 0.01205 -0.0668 0.9445 0.0160
-11.000 -0.8483 0.01717 0.01145 -0.0674 0.9304 0.0164
-10.750 -0.8234 0.01668 0.01088 -0.0677 0.9164 0.0167
-10.500 -0.7983 0.01622 0.01036 -0.0678 0.9026 0.0170
-10.250 -0.7732 0.01582 0.00988 -0.0679 0.8885 0.0172
-10.000 -0.7480 0.01545 0.00942 -0.0678 0.8741 0.0175
-9.750 -0.7224 0.01499 0.00892 -0.0680 0.8624 0.0179
-9.500 -0.6962 0.01463 0.00851 -0.0681 0.8519 0.0183
-9.250 -0.6689 0.01427 0.00813 -0.0684 0.8439 0.0187
-9.000 -0.6416 0.01396 0.00777 -0.0686 0.8349 0.0192
-8.750 -0.6139 0.01366 0.00743 -0.0689 0.8269 0.0196
-8.500 -0.5857 0.01337 0.00710 -0.0692 0.8187 0.0201
-8.250 -0.5574 0.01312 0.00680 -0.0695 0.8113 0.0205
-8.000 -0.5289 0.01279 0.00645 -0.0699 0.8056 0.0211
-7.750 -0.5000 0.01250 0.00616 -0.0704 0.7987 0.0219
-7.500 -0.4711 0.01226 0.00588 -0.0707 0.7904 0.0226
-7.250 -0.4418 0.01203 0.00562 -0.0712 0.7844 0.0233
-7.000 -0.4121 0.01179 0.00537 -0.0717 0.7793 0.0239
-6.750 -0.3825 0.01154 0.00511 -0.0722 0.7716 0.0249
-6.500 -0.3530 0.01134 0.00487 -0.0726 0.7627 0.0259
-6.250 -0.3228 0.01114 0.00466 -0.0732 0.7557 0.0271
-6.000 -0.2927 0.01093 0.00444 -0.0737 0.7479 0.0286
-5.750 -0.2627 0.01076 0.00424 -0.0742 0.7395 0.0305
-5.500 -0.2323 0.01056 0.00405 -0.0748 0.7283 0.0330
-5.250 -0.2021 0.01040 0.00386 -0.0754 0.7158 0.0366
-5.000 -0.1716 0.01022 0.00368 -0.0760 0.7022 0.0423
-4.750 -0.1412 0.01005 0.00350 -0.0766 0.6826 0.0521
-4.500 -0.1116 0.00996 0.00333 -0.0771 0.6418 0.0656
-4.250 -0.0868 0.01046 0.00330 -0.0769 0.4882 0.0808
-4.000 -0.0567 0.01042 0.00321 -0.0776 0.4522 0.1009
-3.750 -0.0258 0.01032 0.00311 -0.0785 0.4303 0.1232
-3.500 0.0057 0.01016 0.00300 -0.0795 0.4132 0.1523
-3.250 0.0378 0.00994 0.00288 -0.0806 0.4001 0.1923
-3.000 0.0704 0.00971 0.00277 -0.0819 0.3903 0.2357
-2.750 0.1037 0.00944 0.00267 -0.0833 0.3817 0.2922
-2.250 0.1741 0.00863 0.00240 -0.0874 0.3648 0.4689
-2.000 0.2089 0.00834 0.00237 -0.0892 0.3577 0.5540
-1.500 0.2711 0.00840 0.00246 -0.0904 0.3454 0.5998
-1.250 0.3017 0.00847 0.00250 -0.0908 0.3393 0.6117
-1.000 0.3321 0.00855 0.00256 -0.0912 0.3331 0.6238
-0.750 0.3624 0.00865 0.00260 -0.0916 0.3280 0.6304
-0.500 0.3928 0.00870 0.00265 -0.0920 0.3236 0.6354
-0.250 0.4229 0.00878 0.00270 -0.0923 0.3182 0.6394
0.000 0.4529 0.00888 0.00275 -0.0927 0.3128 0.6424
0.250 0.4829 0.00897 0.00280 -0.0930 0.3082 0.6448
0.500 0.5130 0.00904 0.00285 -0.0934 0.3043 0.6473
0.750 0.5430 0.00914 0.00290 -0.0937 0.2995 0.6501
1.000 0.5727 0.00924 0.00298 -0.0940 0.2948 0.6548
1.250 0.6024 0.00935 0.00307 -0.0943 0.2900 0.6599
1.500 0.6322 0.00943 0.00315 -0.0946 0.2866 0.6640
1.750 0.6619 0.00953 0.00323 -0.0948 0.2825 0.6665
2.000 0.6913 0.00965 0.00331 -0.0951 0.2779 0.6684
2.250 0.7206 0.00978 0.00339 -0.0953 0.2728 0.6699
2.500 0.7502 0.00987 0.00347 -0.0956 0.2699 0.6711
2.750 0.7797 0.00998 0.00356 -0.0959 0.2661 0.6721
3.000 0.8088 0.01009 0.00365 -0.0961 0.2615 0.6738
3.250 0.8377 0.01023 0.00376 -0.0963 0.2569 0.6759
3.500 0.8668 0.01033 0.00387 -0.0965 0.2536 0.6777
3.750 0.8959 0.01045 0.00398 -0.0967 0.2498 0.6793
4.000 0.9246 0.01058 0.00410 -0.0969 0.2454 0.6808
4.250 0.9530 0.01075 0.00424 -0.0970 0.2406 0.6824
4.500 0.9817 0.01088 0.00437 -0.0972 0.2372 0.6839
4.750 1.0103 0.01101 0.00450 -0.0973 0.2333 0.6857
5.000 1.0384 0.01118 0.00465 -0.0974 0.2288 0.6875
5.250 1.0663 0.01137 0.00481 -0.0974 0.2242 0.6892
5.500 1.0946 0.01151 0.00495 -0.0975 0.2210 0.6907
5.750 1.1225 0.01168 0.00511 -0.0975 0.2167 0.6921
6.000 1.1499 0.01189 0.00529 -0.0975 0.2120 0.6933
6.250 1.1774 0.01207 0.00546 -0.0975 0.2080 0.6945
6.500 1.2050 0.01224 0.00565 -0.0975 0.2039 0.6966
6.750 1.2319 0.01246 0.00585 -0.0974 0.1990 0.6986
7.000 1.2587 0.01267 0.00606 -0.0973 0.1948 0.7006
7.250 1.2856 0.01287 0.00627 -0.0972 0.1907 0.7025
7.500 1.3119 0.01311 0.00650 -0.0969 0.1858 0.7046
7.750 1.3380 0.01336 0.00675 -0.0967 0.1814 0.7069
8.000 1.3640 0.01359 0.00698 -0.0965 0.1768 0.7093
8.250 1.3892 0.01389 0.00726 -0.0961 0.1717 0.7115
8.500 1.4147 0.01414 0.00752 -0.0958 0.1673 0.7134
8.750 1.4395 0.01443 0.00779 -0.0954 0.1623 0.7151
9.000 1.4638 0.01475 0.00810 -0.0949 0.1577 0.7168
9.250 1.4882 0.01503 0.00840 -0.0944 0.1531 0.7194
9.750 1.5349 0.01571 0.00908 -0.0931 0.1437 0.7245
10.000 1.5569 0.01609 0.00946 -0.0923 0.1386 0.7271
10.250 1.5789 0.01645 0.00983 -0.0914 0.1344 0.7297
10.500 1.5998 0.01685 0.01023 -0.0904 0.1297 0.7323
10.750 1.6198 0.01726 0.01065 -0.0892 0.1256 0.7348
11.000 1.6390 0.01769 0.01108 -0.0879 0.1211 0.7370
11.250 1.6544 0.01816 0.01155 -0.0859 0.1174 0.7395
11.500 1.6710 0.01860 0.01203 -0.0841 0.1138 0.7425
11.750 1.6868 0.01918 0.01262 -0.0824 0.1097 0.7456
12.000 1.7036 0.01972 0.01319 -0.0809 0.1062 0.7490
12.250 1.7186 0.02038 0.01385 -0.0792 0.1019 0.7524
12.500 1.7336 0.02105 0.01454 -0.0775 0.0977 0.7556
13.000 1.7605 0.02262 0.01614 -0.0741 0.0892 0.7610
13.250 1.7723 0.02354 0.01708 -0.0724 0.0852 0.7642
13.500 1.7842 0.02448 0.01804 -0.0707 0.0810 0.7674
13.750 1.7950 0.02552 0.01911 -0.0691 0.0776 0.7708
14.000 1.8061 0.02658 0.02020 -0.0676 0.0746 0.7740
14.250 1.8157 0.02776 0.02142 -0.0660 0.0721 0.7770
14.500 1.8261 0.02893 0.02263 -0.0646 0.0697 0.7796
14.750 1.8341 0.03032 0.02407 -0.0632 0.0672 0.7828
15.000 1.8422 0.03173 0.02553 -0.0618 0.0650 0.7862
15.250 1.8492 0.03327 0.02713 -0.0605 0.0628 0.7896
15.500 1.8532 0.03512 0.02902 -0.0592 0.0606 0.7930
15.750 1.8591 0.03686 0.03083 -0.0581 0.0587 0.7962
16.000 1.8623 0.03887 0.03290 -0.0570 0.0569 0.7992
16.250 1.8631 0.04117 0.03527 -0.0560 0.0553 0.8026
16.500 1.8650 0.04347 0.03766 -0.0552 0.0538 0.8065
16.750 1.8642 0.04612 0.04039 -0.0546 0.0523 0.8105
17.000 1.8601 0.04924 0.04359 -0.0540 0.0509 0.8142
17.250 1.8560 0.05252 0.04697 -0.0538 0.0497 0.8176
17.500 1.8504 0.05614 0.05069 -0.0539 0.0485 0.8209
17.750 1.8403 0.06050 0.05517 -0.0544 0.0474 0.8245
18.000 1.8260 0.06565 0.06044 -0.0553 0.0464 0.8280
18.250 1.8083 0.07155 0.06649 -0.0569 0.0456 0.8314
18.500 1.7888 0.07791 0.07299 -0.0587 0.0449 0.8344
19.000 1.7365 0.09261 0.08800 -0.0634 0.0437 0.8398
19.250 1.7078 0.10026 0.09580 -0.0660 0.0431 0.8427
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)