NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.71 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0215f-il-1000000.txt Download as CSV file: xf-nlf0215f-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(1)-0215F 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1254 0.09492 0.09327 -0.0844 0.9798 0.0142
-11.250 -0.1192 0.09095 0.08930 -0.0865 0.9755 0.0144
-11.000 -0.1246 0.08800 0.08637 -0.0853 0.9582 0.0145
-10.750 -0.1178 0.08329 0.08165 -0.0884 0.9451 0.0148
-10.500 -0.1048 0.07728 0.07562 -0.0941 0.9374 0.0152
-10.250 -0.0929 0.06964 0.06794 -0.1018 0.9310 0.0157
-10.000 -0.1053 0.05572 0.05399 -0.1123 0.9266 0.0168
-9.500 -0.2047 0.07000 0.06831 -0.1011 0.9382 0.0149
-9.250 -0.1947 0.05250 0.05061 -0.1285 0.9233 0.0151
-9.000 -0.1964 0.03817 0.03530 -0.1490 0.8641 0.0168
-8.750 -0.2068 0.03579 0.03250 -0.1466 0.8253 0.0168
-8.500 -0.2297 0.03021 0.02644 -0.1438 0.7998 0.0171
-8.250 -0.2193 0.02834 0.02443 -0.1426 0.7826 0.0174
-8.000 -0.2042 0.02720 0.02319 -0.1418 0.7679 0.0176
-7.750 -0.1896 0.02571 0.02152 -0.1409 0.7551 0.0178
-7.500 -0.1721 0.02465 0.02030 -0.1402 0.7435 0.0183
-7.250 -0.1685 0.01685 0.01141 -0.1371 0.7344 0.0142
-7.000 -0.1460 0.01573 0.01008 -0.1364 0.7257 0.0141
-6.750 -0.1223 0.01483 0.00904 -0.1359 0.7177 0.0140
-6.500 -0.0983 0.01418 0.00830 -0.1355 0.7103 0.0142
-6.250 -0.0737 0.01349 0.00754 -0.1351 0.7037 0.0143
-6.000 -0.0488 0.01307 0.00705 -0.1349 0.6972 0.0146
-5.750 -0.0231 0.01264 0.00658 -0.1347 0.6915 0.0150
-5.500 0.0025 0.01219 0.00608 -0.1345 0.6857 0.0153
-5.250 0.0280 0.01175 0.00557 -0.1343 0.6803 0.0156
-5.000 0.0546 0.01133 0.00511 -0.1344 0.6758 0.0159
-4.750 0.0819 0.01100 0.00474 -0.1345 0.6712 0.0164
-4.500 0.1093 0.01076 0.00445 -0.1347 0.6669 0.0168
-4.250 0.1366 0.01029 0.00390 -0.1350 0.6625 0.0174
-4.000 0.1653 0.00994 0.00355 -0.1355 0.6591 0.0181
-3.750 0.1941 0.00972 0.00331 -0.1360 0.6552 0.0188
-3.500 0.2228 0.00954 0.00310 -0.1363 0.6514 0.0198
-3.250 0.2514 0.00942 0.00293 -0.1367 0.6478 0.0207
-3.000 0.2809 0.00920 0.00270 -0.1373 0.6447 0.0235
-2.750 0.3104 0.00903 0.00253 -0.1378 0.6417 0.0275
-2.500 0.3415 0.00855 0.00234 -0.1391 0.6386 0.1011
-2.250 0.3746 0.00785 0.00215 -0.1412 0.6354 0.2685
-2.000 0.4134 0.00661 0.00193 -0.1452 0.6324 0.6088
-1.750 0.4425 0.00677 0.00211 -0.1454 0.6293 0.6616
-1.500 0.4713 0.00692 0.00225 -0.1455 0.6268 0.6762
-1.250 0.4994 0.00708 0.00242 -0.1454 0.6242 0.6847
-1.000 0.5269 0.00737 0.00271 -0.1451 0.6215 0.6971
-0.750 0.5538 0.00767 0.00301 -0.1446 0.6188 0.7055
-0.500 0.5804 0.00793 0.00326 -0.1441 0.6159 0.7129
-0.250 0.6071 0.00819 0.00352 -0.1436 0.6131 0.7178
0.000 0.6355 0.00825 0.00358 -0.1438 0.6110 0.7203
0.250 0.6645 0.00827 0.00359 -0.1441 0.6086 0.7218
0.500 0.6935 0.00829 0.00359 -0.1445 0.6060 0.7230
0.750 0.7225 0.00833 0.00359 -0.1449 0.6035 0.7240
1.000 0.7514 0.00839 0.00361 -0.1452 0.6007 0.7247
1.250 0.7806 0.00849 0.00366 -0.1457 0.5974 0.7253
1.500 0.8092 0.00841 0.00360 -0.1460 0.5950 0.7262
1.750 0.8376 0.00838 0.00358 -0.1462 0.5918 0.7268
2.000 0.8656 0.00838 0.00358 -0.1464 0.5880 0.7275
2.250 0.8933 0.00843 0.00359 -0.1465 0.5836 0.7282
2.500 0.9213 0.00846 0.00362 -0.1466 0.5794 0.7287
2.750 0.9493 0.00845 0.00364 -0.1468 0.5755 0.7292
3.000 0.9771 0.00847 0.00366 -0.1469 0.5715 0.7297
3.250 1.0042 0.00856 0.00371 -0.1469 0.5664 0.7304
3.500 1.0319 0.00857 0.00376 -0.1470 0.5619 0.7311
3.750 1.0596 0.00858 0.00379 -0.1471 0.5572 0.7316
4.000 1.0866 0.00865 0.00384 -0.1471 0.5522 0.7321
4.250 1.1139 0.00870 0.00390 -0.1472 0.5470 0.7327
4.500 1.1413 0.00872 0.00395 -0.1472 0.5411 0.7332
4.750 1.1675 0.00881 0.00402 -0.1471 0.5347 0.7337
5.000 1.1948 0.00884 0.00409 -0.1471 0.5278 0.7343
5.250 1.2206 0.00894 0.00417 -0.1469 0.5194 0.7348
5.500 1.2470 0.00901 0.00425 -0.1468 0.5100 0.7355
5.750 1.2722 0.00913 0.00436 -0.1464 0.4988 0.7363
6.000 1.2965 0.00928 0.00449 -0.1459 0.4839 0.7369
6.250 1.3195 0.00950 0.00464 -0.1452 0.4631 0.7374
6.500 1.3403 0.00983 0.00487 -0.1440 0.4378 0.7379
6.750 1.3584 0.01029 0.00518 -0.1424 0.4042 0.7384
7.000 1.3730 0.01093 0.00561 -0.1402 0.3637 0.7390
7.250 1.3861 0.01158 0.00606 -0.1377 0.3250 0.7395
7.500 1.3970 0.01221 0.00652 -0.1347 0.2915 0.7399
7.750 1.4080 0.01283 0.00699 -0.1318 0.2623 0.7404
8.000 1.4193 0.01348 0.00751 -0.1291 0.2358 0.7408
8.250 1.4307 0.01410 0.00802 -0.1264 0.2128 0.7413
8.500 1.4427 0.01470 0.00854 -0.1239 0.1930 0.7421
8.750 1.4542 0.01533 0.00908 -0.1214 0.1746 0.7429
9.000 1.4649 0.01600 0.00969 -0.1188 0.1577 0.7437
9.250 1.4757 0.01667 0.01032 -0.1162 0.1442 0.7445
9.500 1.4863 0.01738 0.01099 -0.1138 0.1321 0.7452
9.750 1.4960 0.01816 0.01174 -0.1113 0.1208 0.7458
10.250 1.5146 0.01986 0.01340 -0.1065 0.1013 0.7471
10.500 1.5236 0.02080 0.01433 -0.1043 0.0930 0.7478
10.750 1.5299 0.02194 0.01543 -0.1018 0.0841 0.7485
11.000 1.5389 0.02299 0.01649 -0.0999 0.0775 0.7492
11.250 1.5464 0.02419 0.01770 -0.0979 0.0710 0.7499
11.500 1.5542 0.02543 0.01894 -0.0961 0.0657 0.7506
11.750 1.5617 0.02677 0.02029 -0.0944 0.0607 0.7513
12.000 1.5706 0.02806 0.02161 -0.0929 0.0570 0.7520
12.250 1.5765 0.02963 0.02318 -0.0913 0.0527 0.7527
12.500 1.5857 0.03100 0.02461 -0.0901 0.0500 0.7534
12.750 1.5928 0.03258 0.02621 -0.0889 0.0468 0.7541
13.000 1.5978 0.03441 0.02805 -0.0875 0.0431 0.7547
13.250 1.6072 0.03589 0.02959 -0.0866 0.0414 0.7554
13.500 1.6137 0.03766 0.03140 -0.0856 0.0390 0.7559
13.750 1.6185 0.03966 0.03342 -0.0846 0.0364 0.7564
14.000 1.6262 0.04143 0.03525 -0.0838 0.0348 0.7572
14.250 1.6335 0.04325 0.03713 -0.0831 0.0330 0.7582
14.500 1.6385 0.04535 0.03927 -0.0824 0.0312 0.7591
14.750 1.6423 0.04763 0.04159 -0.0817 0.0291 0.7601
15.000 1.6500 0.04954 0.04357 -0.0812 0.0278 0.7611
15.250 1.6551 0.05177 0.04585 -0.0808 0.0262 0.7620
15.500 1.6578 0.05430 0.04843 -0.0803 0.0244 0.7628
15.750 1.6635 0.05656 0.05075 -0.0800 0.0231 0.7637
16.000 1.6678 0.05901 0.05326 -0.0798 0.0215 0.7645
16.250 1.6691 0.06188 0.05617 -0.0795 0.0196 0.7654
16.500 1.6736 0.06441 0.05876 -0.0795 0.0181 0.7663
16.750 1.6742 0.06746 0.06186 -0.0794 0.0162 0.7671
17.000 1.6757 0.07047 0.06493 -0.0795 0.0146 0.7680
17.250 1.6751 0.07382 0.06832 -0.0797 0.0131 0.7688
17.500 1.6744 0.07726 0.07184 -0.0800 0.0118 0.7695
17.750 1.6739 0.08071 0.07536 -0.0804 0.0109 0.7703
18.000 1.6705 0.08465 0.07936 -0.0810 0.0100 0.7710
18.250 1.6682 0.08851 0.08331 -0.0817 0.0095 0.7716
18.500 1.6670 0.09226 0.08716 -0.0825 0.0090 0.7725
18.750 1.6645 0.09626 0.09126 -0.0835 0.0086 0.7736
19.000 1.6599 0.10064 0.09574 -0.0846 0.0082 0.7746
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Polar data table (+)
Polar graphs
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