NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 50,000 Max Cl/Cd: 21.1 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf415-il-50000-n5.txt Download as CSV file: xf-nlf415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(2)-0415 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5860 0.11377 0.10724 -0.0477 0.9976 0.0513
-10.250 -0.5928 0.10927 0.10275 -0.0486 0.9967 0.0503
-10.000 -0.6053 0.10448 0.09796 -0.0499 0.9957 0.0494
-9.750 -0.6214 0.09968 0.09313 -0.0513 0.9945 0.0487
-9.500 -0.6413 0.09517 0.08858 -0.0519 0.9930 0.0480
-9.250 -0.6636 0.09130 0.08465 -0.0516 0.9914 0.0475
-9.000 -0.6891 0.08819 0.08147 -0.0499 0.9901 0.0471
-8.750 -0.7129 0.08527 0.07846 -0.0476 0.9891 0.0467
-8.500 -0.7299 0.08179 0.07481 -0.0459 0.9878 0.0461
-8.250 -0.7422 0.07797 0.07075 -0.0445 0.9863 0.0453
-8.000 -0.7499 0.07413 0.06660 -0.0431 0.9850 0.0444
-7.750 -0.7551 0.07043 0.06254 -0.0412 0.9843 0.0435
-7.500 -0.7562 0.06686 0.05853 -0.0392 0.9836 0.0426
-7.250 -0.7523 0.06347 0.05459 -0.0375 0.9825 0.0418
-7.000 -0.7430 0.06037 0.05108 -0.0362 0.9814 0.0417
-6.750 -0.7305 0.05752 0.04802 -0.0354 0.9805 0.0425
-6.500 -0.7170 0.05504 0.04532 -0.0345 0.9799 0.0436
-6.250 -0.7015 0.05268 0.04263 -0.0336 0.9794 0.0447
-6.000 -0.6830 0.05037 0.03996 -0.0327 0.9785 0.0453
-5.750 -0.6618 0.04820 0.03743 -0.0319 0.9775 0.0454
-5.500 -0.6390 0.04625 0.03515 -0.0311 0.9766 0.0456
-5.250 -0.6158 0.04461 0.03324 -0.0301 0.9758 0.0461
-5.000 -0.5924 0.04323 0.03165 -0.0288 0.9753 0.0468
-4.750 -0.5679 0.04230 0.03056 -0.0273 0.9747 0.0477
-4.500 -0.5434 0.04174 0.02984 -0.0256 0.9739 0.0501
-4.250 -0.5195 0.04138 0.02927 -0.0239 0.9729 0.0525
-4.000 -0.5036 0.04060 0.02855 -0.0214 0.9718 0.0549
-3.750 -0.4885 0.03984 0.02774 -0.0193 0.9708 0.0570
-3.500 -0.4727 0.03902 0.02680 -0.0177 0.9696 0.0595
-3.250 -0.4551 0.03818 0.02580 -0.0167 0.9680 0.0629
-3.000 -0.4357 0.03732 0.02480 -0.0164 0.9665 0.0673
-2.750 -0.4146 0.03641 0.02382 -0.0165 0.9652 0.0784
-2.500 -0.3908 0.03499 0.02262 -0.0179 0.9639 0.1095
-2.250 -0.3814 0.03479 0.02469 -0.0141 0.9622 0.6233
-1.750 -0.3888 0.03899 0.02917 0.0081 0.9579 0.7386
-1.500 -0.3832 0.03952 0.02961 0.0149 0.9556 0.7640
-1.250 -0.3587 0.03928 0.02907 0.0141 0.9535 0.7659
-1.000 -0.3325 0.03910 0.02861 0.0129 0.9514 0.7670
-0.750 -0.3043 0.03902 0.02829 0.0113 0.9492 0.7677
-0.500 -0.2746 0.03907 0.02811 0.0094 0.9472 0.7686
-0.250 -0.2491 0.03896 0.02779 0.0083 0.9446 0.7698
0.000 -0.2254 0.03887 0.02757 0.0078 0.9418 0.7708
0.250 -0.1998 0.03888 0.02745 0.0070 0.9390 0.7717
0.500 -0.1720 0.03900 0.02745 0.0056 0.9363 0.7724
0.750 -0.1420 0.03926 0.02758 0.0039 0.9337 0.7732
1.000 -0.1168 0.03935 0.02759 0.0031 0.9303 0.7743
1.250 -0.0927 0.03943 0.02761 0.0025 0.9267 0.7757
1.500 -0.0653 0.03966 0.02778 0.0013 0.9232 0.7773
1.750 -0.0347 0.04004 0.02811 -0.0005 0.9200 0.7787
2.000 -0.0072 0.04032 0.02837 -0.0018 0.9162 0.7800
2.250 0.0174 0.04050 0.02854 -0.0025 0.9115 0.7814
2.500 0.0469 0.04089 0.02892 -0.0042 0.9074 0.7827
2.750 0.0807 0.04147 0.02951 -0.0067 0.9038 0.7842
3.000 0.1014 0.04161 0.02970 -0.0066 0.8979 0.7857
3.250 0.1287 0.04201 0.03017 -0.0076 0.8929 0.7874
3.500 0.1620 0.04265 0.03089 -0.0097 0.8888 0.7894
3.750 0.1814 0.04283 0.03115 -0.0094 0.8817 0.7915
4.000 0.2126 0.04338 0.03181 -0.0111 0.8763 0.7937
4.250 0.2384 0.04380 0.03234 -0.0120 0.8695 0.7959
4.500 0.2679 0.04429 0.03296 -0.0136 0.8628 0.7980
4.750 0.2964 0.04478 0.03360 -0.0148 0.8556 0.8000
5.000 0.3247 0.04522 0.03424 -0.0159 0.8477 0.8021
5.250 0.3508 0.04559 0.03480 -0.0165 0.8386 0.8045
5.500 0.3882 0.04607 0.03551 -0.0189 0.8305 0.8073
5.750 0.4227 0.04575 0.03545 -0.0201 0.8122 0.8104
6.000 0.4752 0.04412 0.03410 -0.0225 0.7834 0.8137
6.250 0.5135 0.04222 0.03249 -0.0225 0.7546 0.8168
6.500 0.5398 0.04083 0.03142 -0.0212 0.7282 0.8203
6.750 0.5587 0.03978 0.03065 -0.0192 0.6975 0.8242
7.000 0.5776 0.03877 0.02991 -0.0171 0.6575 0.8283
7.250 0.5934 0.03793 0.02937 -0.0144 0.6004 0.8320
7.500 0.6624 0.03396 0.02355 -0.0133 0.2805 0.8359
7.750 0.6712 0.03555 0.02464 -0.0114 0.2190 0.8403
8.000 0.6858 0.03685 0.02568 -0.0103 0.1835 0.8453
8.250 0.7046 0.03785 0.02666 -0.0093 0.1599 0.8509
8.500 0.7279 0.03880 0.02756 -0.0091 0.1407 0.8575
8.750 0.7589 0.03950 0.02834 -0.0093 0.1260 0.8647
9.250 0.8543 0.04108 0.03024 -0.0139 0.0980 0.8825
9.500 0.8949 0.04242 0.03185 -0.0157 0.0870 0.8944
9.750 0.9372 0.04447 0.03435 -0.0178 0.0774 0.9099
10.000 0.9709 0.04676 0.03694 -0.0194 0.0701 0.9380
10.250 0.9921 0.04897 0.03957 -0.0194 0.0633 1.0000
10.500 1.0139 0.05188 0.04268 -0.0200 0.0584 1.0000
10.750 1.0231 0.05508 0.04644 -0.0185 0.0541 1.0000
11.000 1.0315 0.05787 0.04950 -0.0173 0.0511 1.0000
11.250 1.0412 0.06047 0.05214 -0.0166 0.0486 1.0000
11.500 1.0322 0.06411 0.05623 -0.0135 0.0471 1.0000
11.750 1.0187 0.06794 0.06050 -0.0105 0.0461 1.0000
12.000 1.0027 0.07191 0.06482 -0.0078 0.0453 1.0000
12.250 0.9836 0.07615 0.06937 -0.0055 0.0447 1.0000
12.500 0.9628 0.08072 0.07421 -0.0040 0.0445 1.0000
12.750 0.9395 0.08577 0.07950 -0.0032 0.0445 1.0000
13.000 0.9151 0.09136 0.08528 -0.0034 0.0447 1.0000
13.250 0.8893 0.09771 0.09179 -0.0049 0.0451 1.0000
13.500 0.8639 0.10495 0.09915 -0.0079 0.0456 1.0000
13.750 0.8409 0.11309 0.10735 -0.0124 0.0463 1.0000
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Polar data table (+)
Polar graphs
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