NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 1,000,000 Max Cl/Cd: 154.56 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf1015-il-1000000-n5.txt Download as CSV file: xf-nlf1015-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.0628 0.12874 0.12689 -0.1138 0.9436 0.0067
-15.250 -0.0515 0.12531 0.12343 -0.1174 0.9411 0.0068
-15.000 -0.1974 0.13909 0.13717 -0.1013 0.9755 0.0065
-14.500 -0.1938 0.13225 0.13035 -0.1025 0.9641 0.0065
-14.250 -0.1903 0.12845 0.12655 -0.1038 0.9578 0.0065
-14.000 -0.1857 0.12341 0.12149 -0.1066 0.9525 0.0065
-13.000 -0.3581 0.05066 0.04828 -0.1555 0.9333 0.0069
-12.750 -0.3572 0.03891 0.03609 -0.1749 0.9228 0.0068
-12.500 -0.3436 0.03347 0.03030 -0.1853 0.9057 0.0069
-12.250 -0.3401 0.03052 0.02708 -0.1884 0.8860 0.0069
-12.000 -0.3467 0.02793 0.02423 -0.1884 0.8685 0.0069
-11.750 -0.3403 0.02685 0.02304 -0.1878 0.8562 0.0070
-11.500 -0.3398 0.02542 0.02144 -0.1865 0.8448 0.0071
-11.250 -0.3373 0.02428 0.02016 -0.1850 0.8349 0.0072
-11.000 -0.3361 0.02309 0.01884 -0.1830 0.8265 0.0072
-10.750 -0.3367 0.02213 0.01775 -0.1802 0.8189 0.0073
-10.500 -0.3323 0.02102 0.01649 -0.1782 0.8121 0.0074
-10.250 -0.3221 0.02006 0.01537 -0.1767 0.8064 0.0074
-10.000 -0.3086 0.01912 0.01430 -0.1755 0.8016 0.0076
-9.750 -0.2936 0.01821 0.01325 -0.1745 0.7967 0.0076
-9.500 -0.2772 0.01738 0.01229 -0.1734 0.7921 0.0077
-9.250 -0.2579 0.01673 0.01153 -0.1728 0.7881 0.0079
-9.000 -0.2385 0.01601 0.01071 -0.1721 0.7838 0.0080
-8.750 -0.2181 0.01538 0.00997 -0.1715 0.7798 0.0082
-8.250 -0.1740 0.01430 0.00871 -0.1707 0.7733 0.0085
-8.000 -0.1508 0.01382 0.00816 -0.1705 0.7701 0.0087
-7.750 -0.1271 0.01339 0.00767 -0.1703 0.7669 0.0088
-7.500 -0.1029 0.01301 0.00722 -0.1701 0.7639 0.0089
-7.250 -0.0785 0.01264 0.00677 -0.1699 0.7611 0.0090
-7.000 -0.0531 0.01228 0.00638 -0.1700 0.7585 0.0091
-6.750 -0.0292 0.01161 0.00563 -0.1699 0.7556 0.0093
-6.500 -0.0040 0.01115 0.00512 -0.1700 0.7527 0.0096
-6.250 0.0221 0.01080 0.00472 -0.1702 0.7500 0.0098
-6.000 0.0487 0.01050 0.00437 -0.1704 0.7476 0.0101
-5.750 0.0759 0.01025 0.00410 -0.1707 0.7455 0.0104
-5.500 0.1035 0.01000 0.00382 -0.1710 0.7434 0.0108
-5.250 0.1313 0.00978 0.00358 -0.1714 0.7412 0.0113
-5.000 0.1593 0.00957 0.00334 -0.1718 0.7390 0.0117
-4.750 0.1873 0.00938 0.00312 -0.1722 0.7368 0.0122
-4.500 0.2153 0.00923 0.00292 -0.1725 0.7346 0.0125
-4.250 0.2435 0.00908 0.00274 -0.1729 0.7325 0.0129
-4.000 0.2721 0.00891 0.00254 -0.1734 0.7306 0.0138
-3.750 0.3009 0.00877 0.00239 -0.1739 0.7288 0.0149
-3.500 0.3297 0.00865 0.00227 -0.1744 0.7270 0.0163
-3.250 0.3589 0.00844 0.00212 -0.1751 0.7251 0.0348
-3.000 0.3884 0.00818 0.00200 -0.1759 0.7232 0.0742
-2.750 0.4182 0.00792 0.00190 -0.1768 0.7213 0.1252
-2.500 0.4482 0.00766 0.00181 -0.1778 0.7194 0.1863
-2.250 0.4784 0.00745 0.00175 -0.1788 0.7175 0.2444
-2.000 0.5098 0.00714 0.00169 -0.1802 0.7160 0.3289
-1.750 0.5444 0.00654 0.00162 -0.1826 0.7146 0.5070
-1.500 0.5747 0.00643 0.00167 -0.1835 0.7128 0.5706
-1.250 0.6038 0.00644 0.00169 -0.1839 0.7109 0.5869
-1.000 0.6327 0.00646 0.00172 -0.1844 0.7090 0.5985
-0.750 0.6614 0.00649 0.00174 -0.1847 0.7072 0.6064
-0.500 0.6901 0.00652 0.00177 -0.1851 0.7054 0.6140
-0.250 0.7187 0.00657 0.00180 -0.1855 0.7034 0.6208
0.000 0.7474 0.00661 0.00184 -0.1858 0.7015 0.6273
0.250 0.7757 0.00664 0.00188 -0.1861 0.6994 0.6335
0.500 0.8037 0.00666 0.00192 -0.1864 0.6965 0.6388
0.750 0.8313 0.00669 0.00197 -0.1865 0.6932 0.6438
1.000 0.8586 0.00675 0.00201 -0.1866 0.6896 0.6489
1.250 0.8859 0.00680 0.00206 -0.1866 0.6862 0.6533
1.500 0.9133 0.00682 0.00211 -0.1867 0.6825 0.6569
1.750 0.9402 0.00687 0.00216 -0.1867 0.6782 0.6597
2.000 0.9665 0.00693 0.00222 -0.1866 0.6740 0.6623
2.250 0.9934 0.00698 0.00228 -0.1866 0.6699 0.6648
2.500 1.0199 0.00702 0.00234 -0.1865 0.6650 0.6672
2.750 1.0454 0.00709 0.00241 -0.1862 0.6599 0.6694
3.000 1.0712 0.00714 0.00249 -0.1860 0.6543 0.6718
3.250 1.0959 0.00721 0.00257 -0.1855 0.6469 0.6744
3.500 1.1201 0.00729 0.00266 -0.1850 0.6394 0.6773
3.750 1.1422 0.00739 0.00275 -0.1839 0.6301 0.6801
4.250 1.1818 0.00766 0.00299 -0.1809 0.6018 0.6852
4.500 1.1933 0.00801 0.00322 -0.1777 0.5710 0.6881
4.750 1.1949 0.00873 0.00369 -0.1725 0.5168 0.6912
5.000 1.1979 0.00952 0.00423 -0.1678 0.4678 0.6946
5.500 1.2072 0.01112 0.00540 -0.1594 0.3771 0.7012
5.750 1.2134 0.01191 0.00602 -0.1557 0.3372 0.7047
6.000 1.2182 0.01281 0.00672 -0.1519 0.2963 0.7083
6.250 1.2228 0.01376 0.00748 -0.1481 0.2569 0.7119
6.500 1.2272 0.01477 0.00831 -0.1445 0.2173 0.7153
6.750 1.2307 0.01590 0.00924 -0.1408 0.1771 0.7191
7.000 1.2367 0.01696 0.01015 -0.1377 0.1452 0.7233
7.250 1.2454 0.01794 0.01102 -0.1351 0.1196 0.7276
7.500 1.2535 0.01900 0.01196 -0.1325 0.0937 0.7318
7.750 1.2631 0.02003 0.01291 -0.1302 0.0723 0.7365
8.000 1.2702 0.02125 0.01401 -0.1276 0.0484 0.7412
8.250 1.2784 0.02245 0.01511 -0.1253 0.0294 0.7456
8.500 1.2860 0.02374 0.01633 -0.1230 0.0119 0.7504
8.750 1.2988 0.02471 0.01731 -0.1214 0.0078 0.7556
9.000 1.3138 0.02556 0.01819 -0.1201 0.0068 0.7606
9.250 1.3288 0.02640 0.01910 -0.1188 0.0062 0.7662
9.500 1.3440 0.02726 0.02001 -0.1177 0.0059 0.7724
9.750 1.3584 0.02818 0.02099 -0.1164 0.0056 0.7786
10.000 1.3729 0.02911 0.02198 -0.1153 0.0054 0.7857
10.250 1.3865 0.03014 0.02307 -0.1140 0.0052 0.7925
10.500 1.3994 0.03123 0.02423 -0.1127 0.0049 0.7999
10.750 1.4117 0.03239 0.02545 -0.1114 0.0046 0.8072
11.000 1.4224 0.03372 0.02686 -0.1100 0.0043 0.8155
11.250 1.4355 0.03484 0.02806 -0.1089 0.0043 0.8242
11.500 1.4480 0.03605 0.02934 -0.1078 0.0042 0.8341
11.750 1.4601 0.03728 0.03066 -0.1066 0.0041 0.8450
12.000 1.4713 0.03861 0.03207 -0.1054 0.0040 0.8581
12.250 1.4821 0.03995 0.03353 -0.1042 0.0039 0.8745
12.500 1.4911 0.04135 0.03504 -0.1027 0.0038 0.8986
12.750 1.4955 0.04254 0.03639 -0.1004 0.0037 1.0000
13.000 1.5052 0.04417 0.03808 -0.0993 0.0037 1.0000
13.250 1.5146 0.04585 0.03983 -0.0984 0.0036 1.0000
13.500 1.5232 0.04765 0.04168 -0.0974 0.0035 1.0000
13.750 1.5318 0.04947 0.04357 -0.0965 0.0034 1.0000
14.000 1.5391 0.05147 0.04564 -0.0956 0.0034 1.0000
14.250 1.5465 0.05349 0.04774 -0.0947 0.0033 1.0000
14.500 1.5531 0.05562 0.04994 -0.0940 0.0032 1.0000
14.750 1.5594 0.05782 0.05221 -0.0932 0.0032 1.0000
15.000 1.5642 0.06024 0.05471 -0.0925 0.0031 1.0000
15.250 1.5693 0.06268 0.05722 -0.0919 0.0031 1.0000
15.500 1.5726 0.06538 0.06001 -0.0913 0.0030 1.0000
15.750 1.5751 0.06825 0.06296 -0.0909 0.0030 1.0000
16.000 1.5765 0.07129 0.06609 -0.0905 0.0029 1.0000
16.250 1.5762 0.07463 0.06953 -0.0902 0.0029 1.0000
16.500 1.5740 0.07831 0.07331 -0.0900 0.0028 1.0000
16.750 1.5701 0.08233 0.07745 -0.0900 0.0028 1.0000
17.000 1.5638 0.08680 0.08205 -0.0903 0.0027 1.0000
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