NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 200,000 Max Cl/Cd: 77.17 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf1015-il-200000-n5.txt Download as CSV file: xf-nlf1015-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1928 0.05712 0.05301 -0.1468 0.9140 0.0168
-10.000 -0.2030 0.04856 0.04413 -0.1583 0.9083 0.0167
-9.750 -0.2121 0.04420 0.03954 -0.1620 0.8981 0.0166
-9.500 -0.2210 0.04057 0.03564 -0.1639 0.8887 0.0165
-9.250 -0.2238 0.03720 0.03190 -0.1652 0.8807 0.0166
-9.000 -0.2237 0.03473 0.02912 -0.1644 0.8726 0.0165
-8.750 -0.2145 0.03209 0.02607 -0.1646 0.8669 0.0166
-8.500 -0.2023 0.02987 0.02346 -0.1643 0.8618 0.0167
-8.250 -0.1901 0.02816 0.02144 -0.1632 0.8561 0.0168
-8.000 -0.1691 0.02647 0.01940 -0.1635 0.8524 0.0170
-7.750 -0.1448 0.02466 0.01731 -0.1642 0.8495 0.0172
-7.500 -0.1303 0.02345 0.01602 -0.1627 0.8442 0.0178
-7.250 -0.1080 0.02252 0.01497 -0.1626 0.8403 0.0186
-7.000 -0.0816 0.02160 0.01390 -0.1631 0.8372 0.0194
-6.750 -0.0546 0.02064 0.01279 -0.1636 0.8345 0.0199
-6.500 -0.0367 0.01991 0.01197 -0.1622 0.8301 0.0202
-6.250 -0.0140 0.01917 0.01114 -0.1617 0.8266 0.0206
-6.000 0.0113 0.01845 0.01032 -0.1618 0.8238 0.0211
-5.750 0.0388 0.01778 0.00954 -0.1624 0.8215 0.0217
-5.500 0.0633 0.01726 0.00893 -0.1623 0.8186 0.0223
-5.250 0.0842 0.01674 0.00837 -0.1616 0.8147 0.0232
-5.000 0.1098 0.01629 0.00786 -0.1618 0.8115 0.0245
-4.750 0.1380 0.01592 0.00740 -0.1624 0.8090 0.0276
-4.500 0.1678 0.01551 0.00694 -0.1633 0.8070 0.0318
-4.250 0.1970 0.01511 0.00653 -0.1642 0.8049 0.0419
-4.000 0.2197 0.01469 0.00629 -0.1638 0.8017 0.0795
-3.750 0.2460 0.01422 0.00607 -0.1644 0.7988 0.1458
-3.500 0.2753 0.01359 0.00584 -0.1659 0.7963 0.2522
-3.250 0.3079 0.01280 0.00566 -0.1682 0.7942 0.4155
-3.000 0.3379 0.01259 0.00594 -0.1688 0.7923 0.5599
-2.750 0.3682 0.01274 0.00608 -0.1693 0.7906 0.6085
-2.500 0.3907 0.01292 0.00624 -0.1683 0.7876 0.6267
-2.250 0.4157 0.01308 0.00635 -0.1679 0.7849 0.6417
-2.000 0.4427 0.01321 0.00643 -0.1678 0.7824 0.6550
-1.750 0.4720 0.01332 0.00644 -0.1682 0.7802 0.6667
-1.500 0.5003 0.01342 0.00651 -0.1683 0.7783 0.6753
-1.250 0.5309 0.01352 0.00654 -0.1690 0.7767 0.6847
-1.000 0.5555 0.01368 0.00669 -0.1685 0.7744 0.6928
-0.750 0.5780 0.01385 0.00685 -0.1676 0.7712 0.7002
-0.500 0.6024 0.01399 0.00699 -0.1671 0.7685 0.7063
-0.250 0.6314 0.01409 0.00703 -0.1677 0.7664 0.7131
0.000 0.6592 0.01416 0.00711 -0.1678 0.7644 0.7172
0.250 0.6896 0.01422 0.00714 -0.1685 0.7626 0.7219
0.500 0.7209 0.01429 0.00716 -0.1695 0.7609 0.7267
0.750 0.7397 0.01450 0.00742 -0.1680 0.7573 0.7304
1.000 0.7628 0.01464 0.00760 -0.1673 0.7542 0.7335
1.250 0.7898 0.01474 0.00770 -0.1674 0.7516 0.7370
1.500 0.8203 0.01478 0.00774 -0.1682 0.7493 0.7406
1.750 0.8533 0.01481 0.00774 -0.1696 0.7474 0.7444
2.000 0.8750 0.01497 0.00797 -0.1686 0.7440 0.7472
2.250 0.8948 0.01516 0.00823 -0.1673 0.7398 0.7503
2.500 0.9218 0.01523 0.00832 -0.1674 0.7365 0.7537
2.750 0.9542 0.01522 0.00832 -0.1685 0.7337 0.7577
3.000 0.9834 0.01525 0.00838 -0.1690 0.7306 0.7609
3.250 0.9980 0.01548 0.00872 -0.1666 0.7250 0.7641
3.500 1.0250 0.01549 0.00878 -0.1666 0.7209 0.7676
3.750 1.0598 0.01540 0.00869 -0.1681 0.7175 0.7713
4.000 1.0733 0.01563 0.00905 -0.1655 0.7112 0.7757
4.250 1.0977 0.01564 0.00913 -0.1649 0.7060 0.7793
4.500 1.1311 0.01553 0.00905 -0.1661 0.7019 0.7830
4.750 1.1408 0.01579 0.00942 -0.1628 0.6942 0.7879
5.000 1.1706 0.01567 0.00937 -0.1632 0.6886 0.7916
5.250 1.1794 0.01586 0.00968 -0.1596 0.6805 0.7963
5.500 1.2064 0.01577 0.00964 -0.1594 0.6735 0.8014
5.750 1.2133 0.01603 0.01003 -0.1555 0.6641 0.8071
6.000 1.2327 0.01607 0.01015 -0.1539 0.6552 0.8122
6.250 1.2494 0.01619 0.01037 -0.1518 0.6445 0.8183
6.500 1.2589 0.01647 0.01076 -0.1485 0.6320 0.8242
6.750 1.2715 0.01670 0.01107 -0.1458 0.6174 0.8310
7.000 1.2858 0.01689 0.01131 -0.1433 0.5996 0.8382
7.250 1.2976 0.01716 0.01158 -0.1404 0.5737 0.8463
7.500 1.3088 0.01748 0.01177 -0.1374 0.5358 0.8546
8.000 1.3034 0.01956 0.01332 -0.1273 0.4422 0.8764
8.250 1.2947 0.02101 0.01457 -0.1218 0.3997 0.8914
8.500 1.2852 0.02249 0.01589 -0.1164 0.3623 0.9145
8.750 1.2760 0.02389 0.01716 -0.1113 0.3266 1.0000
9.000 1.2740 0.02583 0.01888 -0.1082 0.2879 1.0000
9.250 1.2746 0.02771 0.02057 -0.1056 0.2513 1.0000
9.500 1.2749 0.02970 0.02237 -0.1031 0.2154 1.0000
9.750 1.2763 0.03170 0.02417 -0.1008 0.1793 1.0000
10.000 1.2801 0.03360 0.02590 -0.0989 0.1490 1.0000
10.250 1.2839 0.03556 0.02769 -0.0971 0.1192 1.0000
10.500 1.2876 0.03759 0.02955 -0.0954 0.0913 1.0000
10.750 1.2933 0.03950 0.03134 -0.0939 0.0690 1.0000
11.000 1.2987 0.04149 0.03324 -0.0924 0.0492 1.0000
11.250 1.3031 0.04364 0.03529 -0.0910 0.0325 1.0000
11.500 1.3076 0.04582 0.03744 -0.0896 0.0218 1.0000
11.750 1.3145 0.04783 0.03948 -0.0884 0.0174 1.0000
12.000 1.3220 0.04982 0.04153 -0.0874 0.0151 1.0000
12.250 1.3296 0.05183 0.04362 -0.0865 0.0136 1.0000
12.500 1.3361 0.05399 0.04587 -0.0855 0.0127 1.0000
12.750 1.3423 0.05622 0.04821 -0.0847 0.0121 1.0000
13.000 1.3486 0.05849 0.05062 -0.0839 0.0117 1.0000
13.250 1.3540 0.06090 0.05316 -0.0831 0.0113 1.0000
13.500 1.3583 0.06348 0.05589 -0.0825 0.0110 1.0000
13.750 1.3618 0.06620 0.05874 -0.0819 0.0107 1.0000
14.000 1.3646 0.06905 0.06173 -0.0813 0.0104 1.0000
14.250 1.3665 0.07208 0.06488 -0.0809 0.0102 1.0000
14.500 1.3677 0.07525 0.06818 -0.0806 0.0100 1.0000
14.750 1.3684 0.07857 0.07161 -0.0805 0.0098 1.0000
15.000 1.3683 0.08202 0.07518 -0.0804 0.0096 1.0000
15.250 1.3676 0.08561 0.07889 -0.0804 0.0095 1.0000
15.500 1.3664 0.08932 0.08271 -0.0806 0.0093 1.0000
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