NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 500,000 Max Cl/Cd: 125.85 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf1015-il-500000-n5.txt Download as CSV file: xf-nlf1015-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2369 0.04034 0.03693 -0.1754 0.9076 0.0098
-11.000 -0.2412 0.03506 0.03126 -0.1820 0.8919 0.0097
-10.750 -0.2435 0.03220 0.02814 -0.1837 0.8776 0.0098
-10.500 -0.2518 0.02961 0.02525 -0.1829 0.8643 0.0098
-10.250 -0.2588 0.02790 0.02332 -0.1806 0.8527 0.0098
-10.000 -0.2606 0.02645 0.02167 -0.1784 0.8438 0.0099
-9.750 -0.2550 0.02489 0.01986 -0.1770 0.8366 0.0099
-9.500 -0.2458 0.02351 0.01827 -0.1756 0.8306 0.0100
-9.250 -0.2323 0.02241 0.01700 -0.1746 0.8249 0.0102
-9.000 -0.2164 0.02123 0.01560 -0.1738 0.8203 0.0103
-8.750 -0.1998 0.02020 0.01441 -0.1729 0.8156 0.0104
-8.500 -0.1812 0.01927 0.01333 -0.1722 0.8110 0.0106
-8.250 -0.1607 0.01841 0.01230 -0.1717 0.8069 0.0108
-8.000 -0.1399 0.01763 0.01139 -0.1711 0.8030 0.0110
-7.750 -0.1187 0.01691 0.01056 -0.1706 0.7990 0.0113
-7.500 -0.0963 0.01626 0.00980 -0.1702 0.7954 0.0116
-7.250 -0.0730 0.01564 0.00906 -0.1699 0.7922 0.0118
-7.000 -0.0495 0.01508 0.00842 -0.1697 0.7893 0.0120
-6.750 -0.0261 0.01458 0.00785 -0.1694 0.7861 0.0122
-6.500 -0.0018 0.01414 0.00734 -0.1692 0.7830 0.0124
-6.250 0.0230 0.01370 0.00684 -0.1692 0.7801 0.0127
-6.000 0.0473 0.01303 0.00609 -0.1693 0.7773 0.0134
-5.750 0.0730 0.01260 0.00563 -0.1694 0.7747 0.0138
-5.500 0.0987 0.01222 0.00521 -0.1695 0.7718 0.0143
-5.250 0.1253 0.01190 0.00484 -0.1697 0.7691 0.0147
-5.000 0.1525 0.01161 0.00450 -0.1700 0.7667 0.0153
-4.750 0.1803 0.01137 0.00419 -0.1704 0.7644 0.0161
-4.500 0.2087 0.01117 0.00392 -0.1709 0.7624 0.0167
-4.250 0.2370 0.01096 0.00367 -0.1714 0.7604 0.0178
-4.000 0.2646 0.01076 0.00345 -0.1717 0.7581 0.0201
-3.750 0.2926 0.01051 0.00326 -0.1722 0.7556 0.0306
-3.500 0.3213 0.01013 0.00306 -0.1729 0.7532 0.0793
-3.250 0.3506 0.00979 0.00290 -0.1739 0.7511 0.1349
-3.000 0.3806 0.00947 0.00277 -0.1750 0.7492 0.2008
-2.750 0.4117 0.00911 0.00265 -0.1764 0.7475 0.2833
-2.500 0.4439 0.00864 0.00252 -0.1782 0.7458 0.3987
-2.250 0.4757 0.00820 0.00262 -0.1798 0.7439 0.5655
-2.000 0.5043 0.00822 0.00268 -0.1802 0.7417 0.5950
-1.750 0.5329 0.00826 0.00270 -0.1805 0.7395 0.6084
-1.500 0.5618 0.00831 0.00272 -0.1809 0.7376 0.6203
-1.250 0.5907 0.00835 0.00276 -0.1813 0.7358 0.6288
-1.000 0.6200 0.00841 0.00277 -0.1818 0.7340 0.6367
-0.750 0.6494 0.00847 0.00281 -0.1823 0.7322 0.6439
-0.500 0.6780 0.00853 0.00285 -0.1827 0.7303 0.6513
-0.250 0.7055 0.00858 0.00293 -0.1828 0.7283 0.6573
0.000 0.7336 0.00863 0.00298 -0.1830 0.7262 0.6635
0.250 0.7616 0.00868 0.00304 -0.1833 0.7240 0.6684
0.500 0.7896 0.00873 0.00311 -0.1835 0.7219 0.6731
0.750 0.8183 0.00880 0.00315 -0.1839 0.7197 0.6778
1.000 0.8478 0.00887 0.00319 -0.1844 0.7175 0.6814
1.250 0.8747 0.00891 0.00327 -0.1844 0.7148 0.6841
1.500 0.9008 0.00895 0.00335 -0.1843 0.7114 0.6866
1.750 0.9274 0.00899 0.00341 -0.1842 0.7078 0.6893
2.000 0.9551 0.00904 0.00346 -0.1844 0.7043 0.6923
2.250 0.9824 0.00911 0.00353 -0.1845 0.7007 0.6952
2.750 1.0330 0.00919 0.00370 -0.1838 0.6917 0.7003
3.000 1.0603 0.00926 0.00376 -0.1839 0.6876 0.7030
3.250 1.0842 0.00931 0.00388 -0.1833 0.6827 0.7061
3.500 1.1089 0.00937 0.00397 -0.1828 0.6773 0.7091
3.750 1.1343 0.00945 0.00406 -0.1825 0.6719 0.7121
4.000 1.1569 0.00950 0.00419 -0.1816 0.6649 0.7148
4.250 1.1803 0.00958 0.00428 -0.1808 0.6581 0.7177
4.500 1.2020 0.00966 0.00443 -0.1797 0.6500 0.7211
4.750 1.2228 0.00975 0.00456 -0.1784 0.6412 0.7249
5.000 1.2409 0.00986 0.00468 -0.1765 0.6300 0.7286
5.250 1.2552 0.01001 0.00484 -0.1738 0.6126 0.7317
5.500 1.2639 0.01032 0.00507 -0.1700 0.5829 0.7354
5.750 1.2667 0.01088 0.00547 -0.1652 0.5442 0.7397
6.250 1.2607 0.01272 0.00688 -0.1538 0.4549 0.7484
6.500 1.2592 0.01377 0.00774 -0.1488 0.4132 0.7534
6.750 1.2572 0.01496 0.00873 -0.1440 0.3703 0.7586
7.000 1.2508 0.01646 0.00996 -0.1387 0.3188 0.7634
7.250 1.2497 0.01785 0.01115 -0.1345 0.2748 0.7687
7.500 1.2483 0.01940 0.01245 -0.1306 0.2290 0.7742
7.750 1.2543 0.02059 0.01354 -0.1278 0.1989 0.7793
8.000 1.2612 0.02181 0.01465 -0.1253 0.1713 0.7853
8.500 1.2763 0.02429 0.01694 -0.1206 0.1210 0.7980
9.000 1.2874 0.02723 0.01964 -0.1159 0.0678 0.8123
9.500 1.2989 0.03036 0.02259 -0.1115 0.0259 0.8281
9.750 1.3051 0.03197 0.02414 -0.1095 0.0119 0.8367
10.000 1.3163 0.03317 0.02539 -0.1080 0.0098 0.8467
10.250 1.3281 0.03432 0.02663 -0.1066 0.0087 0.8580
10.500 1.3397 0.03547 0.02788 -0.1051 0.0081 0.8718
10.750 1.3503 0.03663 0.02915 -0.1035 0.0077 0.8909
11.000 1.3559 0.03765 0.03032 -0.1009 0.0073 0.9419
11.250 1.3654 0.03897 0.03172 -0.0995 0.0070 1.0000
11.500 1.3757 0.04053 0.03335 -0.0984 0.0067 1.0000
11.750 1.3849 0.04222 0.03511 -0.0973 0.0064 1.0000
12.000 1.3959 0.04377 0.03673 -0.0963 0.0063 1.0000
12.250 1.4059 0.04541 0.03846 -0.0954 0.0061 1.0000
12.500 1.4155 0.04712 0.04024 -0.0944 0.0059 1.0000
12.750 1.4242 0.04896 0.04217 -0.0935 0.0057 1.0000
13.000 1.4326 0.05086 0.04415 -0.0926 0.0056 1.0000
13.250 1.4400 0.05290 0.04627 -0.0918 0.0054 1.0000
13.500 1.4465 0.05507 0.04852 -0.0909 0.0053 1.0000
13.750 1.4521 0.05737 0.05091 -0.0901 0.0051 1.0000
14.000 1.4570 0.05979 0.05343 -0.0894 0.0050 1.0000
14.250 1.4614 0.06234 0.05606 -0.0887 0.0049 1.0000
14.500 1.4647 0.06507 0.05888 -0.0881 0.0049 1.0000
14.750 1.4673 0.06794 0.06185 -0.0876 0.0048 1.0000
15.000 1.4688 0.07099 0.06501 -0.0872 0.0047 1.0000
15.250 1.4689 0.07428 0.06841 -0.0869 0.0046 1.0000
15.500 1.4682 0.07779 0.07202 -0.0867 0.0045 1.0000
15.750 1.4660 0.08155 0.07589 -0.0866 0.0045 1.0000
16.000 1.4631 0.08550 0.07995 -0.0867 0.0044 1.0000
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