NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 200,000 Max Cl/Cd: 75.63 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf1015-il-200000.txt Download as CSV file: xf-nlf1015-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA NLF1015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0384 0.09372 0.09019 -0.1173 0.9376 0.0612
-10.500 -0.0302 0.08935 0.08581 -0.1206 0.9366 0.0639
-10.250 -0.1477 0.09816 0.09455 -0.1157 0.9493 0.0577
-10.000 -0.1383 0.09648 0.09286 -0.1143 0.9423 0.0599
-9.750 -0.1256 0.09274 0.08911 -0.1178 0.9396 0.0624
-9.500 -0.1209 0.08695 0.08333 -0.1256 0.9373 0.0665
-9.250 -0.1594 0.07792 0.07430 -0.1392 0.9259 0.0681
-9.000 -0.1828 0.07403 0.07032 -0.1429 0.9173 0.0682
-8.750 -0.1148 0.07172 0.06813 -0.1386 0.9241 0.0715
-8.500 -0.0991 0.06723 0.06362 -0.1439 0.9226 0.0741
-8.250 -0.1217 0.06315 0.05953 -0.1456 0.9116 0.0748
-8.000 -0.1462 0.05958 0.05591 -0.1466 0.9017 0.0757
-7.500 -0.1256 0.03667 0.03287 -0.1460 0.8811 0.0858
-7.250 -0.1106 0.03308 0.02914 -0.1483 0.8794 0.0891
-7.000 -0.1728 0.03703 0.03110 -0.1499 0.8781 0.0451
-6.750 -0.1950 0.03680 0.03105 -0.1420 0.8676 0.0467
-6.500 -0.1657 0.03268 0.02645 -0.1434 0.8664 0.0400
-6.250 -0.1326 0.02885 0.02185 -0.1451 0.8654 0.0366
-6.000 -0.1515 0.02943 0.02234 -0.1372 0.8554 0.0364
-5.750 -0.1207 0.02771 0.02037 -0.1382 0.8538 0.0365
-5.500 -0.0881 0.02651 0.01908 -0.1396 0.8527 0.0383
-5.250 -0.0539 0.02535 0.01780 -0.1410 0.8518 0.0398
-5.000 -0.0193 0.02415 0.01648 -0.1424 0.8510 0.0405
-4.750 -0.0398 0.02528 0.01760 -0.1345 0.8414 0.0406
-4.500 -0.0108 0.02449 0.01676 -0.1350 0.8394 0.0420
-4.250 0.0217 0.02377 0.01597 -0.1361 0.8381 0.0440
-4.000 0.0578 0.02272 0.01493 -0.1384 0.8372 0.0482
-3.750 0.0960 0.02199 0.01418 -0.1409 0.8365 0.0589
-3.500 0.1445 0.01986 0.01314 -0.1472 0.8363 0.2829
-3.250 0.1871 0.01884 0.01318 -0.1511 0.8359 0.5466
-3.000 0.1651 0.02072 0.01512 -0.1430 0.8259 0.5714
-2.750 0.1920 0.02112 0.01553 -0.1426 0.8239 0.6327
-2.500 0.2210 0.02142 0.01582 -0.1422 0.8224 0.6684
-2.250 0.2508 0.02164 0.01601 -0.1417 0.8213 0.6940
-2.000 0.2327 0.02358 0.01799 -0.1345 0.8123 0.7023
-1.750 0.2548 0.02398 0.01834 -0.1332 0.8095 0.7172
-1.500 0.2822 0.02419 0.01849 -0.1328 0.8078 0.7308
-1.250 0.3135 0.02427 0.01849 -0.1331 0.8066 0.7439
-1.000 0.3014 0.02587 0.02014 -0.1269 0.7985 0.7505
-0.750 0.3239 0.02624 0.02046 -0.1261 0.7952 0.7609
-0.500 0.3512 0.02632 0.02051 -0.1257 0.7933 0.7705
-0.250 0.3810 0.02629 0.02043 -0.1257 0.7919 0.7795
0.000 0.4170 0.02617 0.02025 -0.1271 0.7910 0.7897
0.250 0.4491 0.02591 0.01998 -0.1272 0.7902 0.7962
0.500 0.4315 0.02795 0.02204 -0.1213 0.7787 0.8038
0.750 0.4634 0.02776 0.02182 -0.1217 0.7772 0.8091
1.000 0.4995 0.02752 0.02155 -0.1231 0.7762 0.8149
1.250 0.5412 0.02719 0.02117 -0.1257 0.7756 0.8202
1.500 0.5785 0.02677 0.02074 -0.1271 0.7750 0.8239
1.750 0.5608 0.02874 0.02276 -0.1210 0.7624 0.8298
2.000 0.6027 0.02838 0.02236 -0.1236 0.7615 0.8342
2.250 0.6422 0.02784 0.02183 -0.1254 0.7608 0.8376
2.500 0.6830 0.02727 0.02127 -0.1275 0.7604 0.8411
2.750 0.6707 0.02916 0.02319 -0.1223 0.7476 0.8473
3.000 0.6749 0.03032 0.02439 -0.1195 0.7384 0.8521
3.250 0.7070 0.03005 0.02415 -0.1201 0.7354 0.8560
3.500 0.7458 0.02952 0.02364 -0.1219 0.7339 0.8607
3.750 0.7888 0.02880 0.02296 -0.1242 0.7330 0.8652
4.000 0.8306 0.02786 0.02207 -0.1260 0.7324 0.8691
4.250 0.8766 0.02681 0.02107 -0.1286 0.7320 0.8733
4.500 0.9265 0.02572 0.02003 -0.1320 0.7316 0.8779
4.750 0.9755 0.02458 0.01896 -0.1352 0.7311 0.8822
5.000 1.0286 0.02338 0.01784 -0.1392 0.7304 0.8866
5.250 1.0152 0.02455 0.01909 -0.1325 0.7182 0.8956
5.500 1.0699 0.02306 0.01769 -0.1365 0.7174 0.9002
5.750 1.1330 0.02154 0.01626 -0.1422 0.7163 0.9046
6.000 1.1199 0.02224 0.01705 -0.1350 0.7049 0.9169
6.250 1.1811 0.02069 0.01559 -0.1403 0.7029 0.9227
6.500 1.1791 0.02089 0.01590 -0.1347 0.6931 0.9380
6.750 1.2304 0.01948 0.01459 -0.1382 0.6886 0.9479
7.000 1.2433 0.01926 0.01450 -0.1355 0.6784 1.0000
7.250 1.3046 0.01790 0.01321 -0.1411 0.6714 1.0000
7.500 1.3204 0.01795 0.01336 -0.1392 0.6582 1.0000
7.750 1.3416 0.01774 0.01321 -0.1382 0.6426 1.0000
8.000 1.3448 0.01817 0.01371 -0.1342 0.6213 1.0000
8.250 1.3567 0.01831 0.01384 -0.1316 0.5929 1.0000
8.500 1.3707 0.01850 0.01387 -0.1292 0.5505 1.0000
8.750 1.3797 0.01919 0.01425 -0.1262 0.5000 1.0000
9.000 1.3781 0.02057 0.01529 -0.1220 0.4510 1.0000
9.250 1.3726 0.02229 0.01675 -0.1176 0.4067 1.0000
9.500 1.3653 0.02426 0.01847 -0.1133 0.3638 1.0000
9.750 1.3588 0.02634 0.02033 -0.1095 0.3238 1.0000
10.250 1.3498 0.03072 0.02430 -0.1030 0.2489 1.0000
10.500 1.3481 0.03291 0.02631 -0.1004 0.2151 1.0000
10.750 1.3463 0.03523 0.02846 -0.0980 0.1811 1.0000
11.000 1.3448 0.03763 0.03066 -0.0958 0.1451 1.0000
11.250 1.3404 0.04039 0.03314 -0.0935 0.1038 1.0000
11.500 1.3278 0.04408 0.03638 -0.0906 0.0549 1.0000
11.750 1.3220 0.04732 0.03948 -0.0883 0.0371 1.0000
12.000 1.3221 0.05008 0.04227 -0.0867 0.0316 1.0000
12.250 1.3263 0.05247 0.04475 -0.0855 0.0285 1.0000
12.500 1.3252 0.05546 0.04780 -0.0841 0.0266 1.0000
12.750 1.3259 0.05835 0.05079 -0.0829 0.0254 1.0000
13.000 1.3303 0.06089 0.05345 -0.0819 0.0244 1.0000
13.250 1.3345 0.06349 0.05618 -0.0810 0.0235 1.0000
13.500 1.3393 0.06607 0.05885 -0.0802 0.0227 1.0000
13.750 1.3448 0.06859 0.06145 -0.0794 0.0220 1.0000
14.000 1.3513 0.07103 0.06394 -0.0787 0.0214 1.0000
14.250 1.3596 0.07329 0.06625 -0.0779 0.0209 1.0000
14.500 1.3737 0.07505 0.06804 -0.0769 0.0203 1.0000
14.750 1.3913 0.07667 0.06976 -0.0760 0.0198 1.0000
15.000 1.3996 0.07911 0.07240 -0.0755 0.0194 1.0000
15.250 1.4070 0.08170 0.07521 -0.0751 0.0189 1.0000
15.500 1.4142 0.08443 0.07814 -0.0747 0.0186 1.0000
15.750 1.4206 0.08740 0.08133 -0.0743 0.0184 1.0000
16.000 1.4235 0.09082 0.08501 -0.0740 0.0183 1.0000
16.250 1.4229 0.09471 0.08915 -0.0740 0.0183 1.0000
16.500 1.4188 0.09906 0.09377 -0.0742 0.0183 1.0000
16.750 1.4116 0.10386 0.09885 -0.0748 0.0184 1.0000
17.000 1.4017 0.10909 0.10434 -0.0758 0.0185 1.0000
17.250 1.3894 0.11477 0.11028 -0.0774 0.0186 1.0000
17.500 1.3754 0.12084 0.11661 -0.0795 0.0187 1.0000
17.750 1.3605 0.12726 0.12327 -0.0822 0.0189 1.0000
18.000 1.3447 0.13408 0.13030 -0.0855 0.0190 1.0000
18.250 1.3274 0.14149 0.13793 -0.0896 0.0192 1.0000
18.500 1.3099 0.14927 0.14591 -0.0942 0.0194 1.0000
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Polar data table (+)
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