NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 1,000,000 Max Cl/Cd: 167.74 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf1015-il-1000000.txt Download as CSV file: xf-nlf1015-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0924 0.08680 0.08494 -0.1339 0.9421 0.0141
-11.000 -0.0796 0.08018 0.07829 -0.1415 0.9381 0.0152
-10.750 -0.1041 0.05465 0.05257 -0.1672 0.9292 0.0164
-10.500 -0.1027 0.04378 0.04131 -0.1876 0.9132 0.0164
-10.250 -0.1089 0.03946 0.03668 -0.1929 0.8914 0.0164
-10.000 -0.1267 0.03694 0.03392 -0.1920 0.8722 0.0164
-9.750 -0.1440 0.03532 0.03212 -0.1888 0.8578 0.0164
-9.500 -0.1532 0.03335 0.02991 -0.1866 0.8473 0.0164
-8.750 -0.1803 0.01985 0.01507 -0.1784 0.8235 0.0127
-8.500 -0.1615 0.01866 0.01369 -0.1778 0.8188 0.0127
-8.250 -0.1410 0.01778 0.01269 -0.1772 0.8146 0.0126
-8.000 -0.1216 0.01633 0.01108 -0.1765 0.8103 0.0128
-7.750 -0.1005 0.01511 0.00973 -0.1760 0.8064 0.0130
-7.500 -0.0784 0.01417 0.00870 -0.1755 0.8028 0.0131
-7.250 -0.0560 0.01341 0.00790 -0.1750 0.7993 0.0133
-7.000 -0.0327 0.01279 0.00722 -0.1747 0.7958 0.0136
-6.750 -0.0082 0.01227 0.00663 -0.1746 0.7924 0.0139
-6.500 0.0174 0.01185 0.00615 -0.1747 0.7891 0.0144
-6.250 0.0421 0.01138 0.00565 -0.1746 0.7862 0.0147
-6.000 0.0678 0.01098 0.00521 -0.1747 0.7834 0.0150
-5.750 0.0943 0.01062 0.00479 -0.1748 0.7806 0.0154
-5.500 0.1216 0.01030 0.00441 -0.1752 0.7779 0.0158
-5.250 0.1503 0.01004 0.00408 -0.1758 0.7752 0.0161
-5.000 0.1775 0.00978 0.00380 -0.1760 0.7730 0.0164
-4.750 0.2050 0.00935 0.00332 -0.1764 0.7706 0.0178
-4.500 0.2331 0.00911 0.00305 -0.1768 0.7681 0.0192
-4.250 0.2616 0.00893 0.00283 -0.1773 0.7657 0.0206
-4.000 0.2907 0.00876 0.00263 -0.1778 0.7634 0.0241
-3.750 0.3211 0.00835 0.00242 -0.1790 0.7612 0.0772
-3.500 0.3514 0.00792 0.00227 -0.1803 0.7592 0.1581
-3.250 0.3815 0.00747 0.00214 -0.1815 0.7573 0.2533
-3.000 0.4125 0.00703 0.00202 -0.1830 0.7553 0.3597
-2.750 0.4445 0.00657 0.00192 -0.1846 0.7532 0.4830
-2.500 0.4751 0.00642 0.00195 -0.1856 0.7512 0.5584
-2.250 0.5049 0.00643 0.00197 -0.1862 0.7493 0.5874
-2.000 0.5349 0.00648 0.00204 -0.1868 0.7474 0.6139
-1.750 0.5653 0.00657 0.00210 -0.1876 0.7452 0.6255
-1.500 0.5937 0.00660 0.00211 -0.1879 0.7436 0.6332
-1.250 0.6222 0.00661 0.00215 -0.1882 0.7417 0.6403
-1.000 0.6510 0.00666 0.00218 -0.1885 0.7398 0.6469
-0.750 0.6799 0.00669 0.00220 -0.1890 0.7379 0.6522
-0.500 0.7086 0.00673 0.00224 -0.1893 0.7359 0.6573
-0.250 0.7378 0.00679 0.00228 -0.1898 0.7340 0.6627
0.000 0.7676 0.00686 0.00233 -0.1904 0.7317 0.6675
0.250 0.7963 0.00692 0.00240 -0.1908 0.7294 0.6722
0.500 0.8235 0.00694 0.00244 -0.1908 0.7270 0.6768
0.750 0.8512 0.00697 0.00247 -0.1910 0.7241 0.6808
1.000 0.8788 0.00698 0.00250 -0.1911 0.7210 0.6848
1.250 0.9071 0.00703 0.00254 -0.1914 0.7180 0.6887
1.500 0.9358 0.00711 0.00261 -0.1918 0.7148 0.6924
1.750 0.9620 0.00712 0.00265 -0.1916 0.7116 0.6954
2.000 0.9889 0.00713 0.00268 -0.1916 0.7081 0.6980
2.250 1.0160 0.00715 0.00272 -0.1916 0.7047 0.7007
2.500 1.0449 0.00724 0.00279 -0.1921 0.7010 0.7033
2.750 1.0702 0.00724 0.00286 -0.1917 0.6976 0.7062
3.000 1.0959 0.00726 0.00291 -0.1914 0.6933 0.7090
3.250 1.1222 0.00731 0.00295 -0.1913 0.6890 0.7117
3.500 1.1487 0.00737 0.00302 -0.1912 0.6846 0.7145
3.750 1.1733 0.00737 0.00311 -0.1907 0.6799 0.7175
4.000 1.1982 0.00742 0.00317 -0.1903 0.6746 0.7206
4.250 1.2230 0.00749 0.00326 -0.1898 0.6691 0.7238
4.500 1.2466 0.00753 0.00335 -0.1891 0.6624 0.7269
4.750 1.2688 0.00760 0.00343 -0.1881 0.6541 0.7301
5.000 1.2866 0.00767 0.00351 -0.1861 0.6407 0.7335
5.250 1.3023 0.00778 0.00362 -0.1837 0.6242 0.7374
5.500 1.3149 0.00801 0.00379 -0.1806 0.6005 0.7415
5.750 1.3183 0.00853 0.00413 -0.1757 0.5574 0.7456
6.000 1.3145 0.00939 0.00473 -0.1696 0.5016 0.7500
6.250 1.3136 0.01029 0.00539 -0.1642 0.4529 0.7547
6.500 1.3167 0.01114 0.00604 -0.1598 0.4110 0.7593
6.750 1.3193 0.01205 0.00677 -0.1555 0.3700 0.7642
7.250 1.3236 0.01410 0.00845 -0.1471 0.2896 0.7751
7.500 1.3243 0.01529 0.00946 -0.1429 0.2479 0.7809
7.750 1.3265 0.01650 0.01049 -0.1392 0.2113 0.7874
8.000 1.3315 0.01764 0.01150 -0.1360 0.1799 0.7936
8.250 1.3363 0.01886 0.01258 -0.1329 0.1493 0.8005
8.500 1.3406 0.02018 0.01375 -0.1299 0.1186 0.8075
8.750 1.3442 0.02159 0.01503 -0.1269 0.0892 0.8153
9.000 1.3466 0.02317 0.01644 -0.1239 0.0582 0.8233
9.250 1.3478 0.02491 0.01802 -0.1209 0.0298 0.8324
9.500 1.3507 0.02659 0.01962 -0.1181 0.0123 0.8421
9.750 1.3633 0.02761 0.02070 -0.1166 0.0104 0.8535
10.000 1.3753 0.02868 0.02183 -0.1150 0.0094 0.8670
10.250 1.3858 0.02983 0.02310 -0.1132 0.0086 0.8838
10.500 1.3966 0.03078 0.02416 -0.1114 0.0083 0.9110
10.750 1.4033 0.03165 0.02517 -0.1088 0.0080 1.0000
11.000 1.4158 0.03288 0.02645 -0.1076 0.0076 1.0000
11.250 1.4278 0.03416 0.02778 -0.1065 0.0073 1.0000
11.500 1.4383 0.03561 0.02927 -0.1052 0.0070 1.0000
11.750 1.4478 0.03715 0.03087 -0.1038 0.0068 1.0000
12.000 1.4553 0.03891 0.03271 -0.1024 0.0066 1.0000
12.250 1.4601 0.04098 0.03487 -0.1008 0.0064 1.0000
12.500 1.4647 0.04310 0.03708 -0.0993 0.0062 1.0000
12.750 1.4737 0.04482 0.03887 -0.0982 0.0062 1.0000
13.000 1.4819 0.04666 0.04077 -0.0971 0.0061 1.0000
13.250 1.4892 0.04862 0.04280 -0.0961 0.0060 1.0000
13.500 1.4957 0.05070 0.04496 -0.0951 0.0059 1.0000
13.750 1.5014 0.05293 0.04727 -0.0941 0.0059 1.0000
14.000 1.5068 0.05521 0.04964 -0.0932 0.0058 1.0000
14.250 1.5107 0.05772 0.05223 -0.0923 0.0057 1.0000
14.500 1.5149 0.06023 0.05482 -0.0915 0.0056 1.0000
14.750 1.5184 0.06288 0.05756 -0.0908 0.0055 1.0000
15.000 1.5212 0.06570 0.06046 -0.0902 0.0054 1.0000
15.250 1.5239 0.06856 0.06341 -0.0897 0.0053 1.0000
15.500 1.5257 0.07157 0.06651 -0.0893 0.0053 1.0000
15.750 1.5268 0.07475 0.06978 -0.0890 0.0052 1.0000
16.000 1.5277 0.07804 0.07316 -0.0888 0.0051 1.0000
16.250 1.5283 0.08141 0.07662 -0.0887 0.0051 1.0000
16.500 1.5281 0.08496 0.08027 -0.0888 0.0050 1.0000
16.750 1.5274 0.08862 0.08404 -0.0890 0.0049 1.0000
17.000 1.5262 0.09241 0.08792 -0.0893 0.0049 1.0000
17.250 1.5248 0.09629 0.09189 -0.0898 0.0048 1.0000
17.500 1.5229 0.10029 0.09598 -0.0905 0.0048 1.0000
17.750 1.5207 0.10439 0.10018 -0.0913 0.0047 1.0000
18.000 1.5178 0.10860 0.10449 -0.0923 0.0046 1.0000
18.250 1.5133 0.11303 0.10902 -0.0933 0.0046 1.0000
18.500 1.5082 0.11755 0.11366 -0.0944 0.0045 1.0000
18.750 1.5029 0.12215 0.11838 -0.0957 0.0044 1.0000
19.000 1.4971 0.12693 0.12330 -0.0973 0.0044 1.0000
19.250 1.4926 0.13162 0.12812 -0.0993 0.0044 1.0000
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