NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.37 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf414f-il-1000000.txt Download as CSV file: xf-nlf414f-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F AIRFOIL
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 -0.3290 0.09783 0.09568 -0.0478 0.8035 0.0149
-11.000 -0.3483 0.08792 0.08579 -0.0522 0.8034 0.0156
-9.000 -0.5238 0.03389 0.03085 -0.0715 0.8004 0.0157
-8.750 -0.5267 0.03003 0.02672 -0.0705 0.8000 0.0157
-8.500 -0.5928 0.02861 0.02414 -0.0666 0.7997 0.0130
-8.250 -0.5728 0.02619 0.02158 -0.0664 0.7993 0.0120
-8.000 -0.5540 0.02325 0.01826 -0.0658 0.7990 0.0119
-7.750 -0.5310 0.02151 0.01629 -0.0656 0.7987 0.0120
-7.500 -0.5064 0.02026 0.01486 -0.0656 0.7984 0.0121
-7.250 -0.4811 0.01921 0.01368 -0.0655 0.7980 0.0122
-7.000 -0.4554 0.01833 0.01268 -0.0655 0.7975 0.0123
-6.750 -0.4293 0.01757 0.01184 -0.0656 0.7972 0.0123
-6.500 -0.4031 0.01691 0.01111 -0.0656 0.7969 0.0124
-6.250 -0.3766 0.01634 0.01049 -0.0657 0.7966 0.0125
-6.000 -0.3501 0.01583 0.00994 -0.0658 0.7963 0.0126
-5.750 -0.3246 0.01512 0.00919 -0.0658 0.7959 0.0127
-5.500 -0.2996 0.01441 0.00845 -0.0658 0.7955 0.0131
-5.250 -0.2731 0.01407 0.00811 -0.0660 0.7949 0.0135
-5.000 -0.2463 0.01384 0.00787 -0.0662 0.7943 0.0139
-4.750 -0.2192 0.01371 0.00773 -0.0665 0.7937 0.0144
-4.500 -0.1912 0.01341 0.00741 -0.0668 0.7933 0.0149
-4.250 -0.1628 0.01314 0.00714 -0.0673 0.7928 0.0156
-4.000 -0.1347 0.01280 0.00679 -0.0677 0.7922 0.0165
-3.750 -0.1062 0.01262 0.00663 -0.0682 0.7916 0.0178
-3.500 -0.0774 0.01248 0.00650 -0.0687 0.7909 0.0192
-3.250 -0.0488 0.01229 0.00633 -0.0692 0.7900 0.0231
-3.000 -0.0204 0.01205 0.00619 -0.0697 0.7891 0.0396
-2.750 0.0075 0.01175 0.00610 -0.0702 0.7883 0.0869
-2.500 0.0345 0.01112 0.00595 -0.0709 0.7874 0.2141
-2.250 0.0609 0.01014 0.00571 -0.0719 0.7864 0.4255
-2.000 0.0872 0.00914 0.00559 -0.0725 0.7856 0.6658
-1.750 0.1164 0.00954 0.00608 -0.0726 0.7849 0.7219
-1.500 0.1457 0.00991 0.00642 -0.0728 0.7842 0.7366
-1.250 0.1752 0.01023 0.00670 -0.0730 0.7835 0.7461
-1.000 0.2027 0.01075 0.00730 -0.0724 0.7828 0.7582
-0.750 0.2295 0.01103 0.00764 -0.0718 0.7821 0.7658
-0.500 0.2582 0.01120 0.00779 -0.0718 0.7814 0.7706
-0.250 0.2880 0.01130 0.00786 -0.0723 0.7807 0.7731
0.000 0.3165 0.01119 0.00773 -0.0726 0.7800 0.7747
0.250 0.3450 0.01119 0.00773 -0.0728 0.7793 0.7759
0.500 0.3727 0.01138 0.00792 -0.0728 0.7779 0.7774
0.750 0.4022 0.01131 0.00789 -0.0734 0.7758 0.7793
1.000 0.4315 0.01125 0.00786 -0.0738 0.7733 0.7813
1.250 0.4612 0.01110 0.00770 -0.0742 0.7713 0.7829
1.500 0.4914 0.01076 0.00734 -0.0745 0.7692 0.7840
1.750 0.5221 0.01023 0.00677 -0.0747 0.7668 0.7850
2.000 0.5527 0.00975 0.00624 -0.0750 0.7645 0.7859
2.250 0.5830 0.00947 0.00594 -0.0754 0.7613 0.7867
2.500 0.6134 0.00916 0.00564 -0.0759 0.7562 0.7873
2.750 0.6442 0.00861 0.00507 -0.0763 0.7513 0.7879
3.000 0.6744 0.00815 0.00460 -0.0767 0.7454 0.7885
3.250 0.7043 0.00791 0.00440 -0.0773 0.7387 0.7889
3.500 0.7341 0.00767 0.00419 -0.0777 0.7305 0.7895
3.750 0.7640 0.00747 0.00402 -0.0782 0.7127 0.7901
4.000 0.7890 0.00756 0.00370 -0.0778 0.6333 0.7906
4.250 0.8045 0.00890 0.00443 -0.0766 0.5037 0.7910
4.500 0.8189 0.01016 0.00516 -0.0753 0.3937 0.7914
4.750 0.8330 0.01125 0.00580 -0.0740 0.3007 0.7918
5.000 0.8468 0.01224 0.00641 -0.0726 0.2224 0.7922
5.250 0.8622 0.01308 0.00699 -0.0715 0.1704 0.7928
5.500 0.8778 0.01371 0.00747 -0.0702 0.1406 0.7934
5.750 0.8970 0.01429 0.00792 -0.0695 0.1152 0.7936
6.000 0.9168 0.01489 0.00838 -0.0689 0.0921 0.7939
6.250 0.9369 0.01544 0.00883 -0.0683 0.0734 0.7940
6.500 0.9563 0.01602 0.00931 -0.0676 0.0590 0.7943
6.750 0.9765 0.01653 0.00976 -0.0669 0.0505 0.7948
7.000 0.9974 0.01699 0.01021 -0.0663 0.0453 0.7951
7.250 1.0166 0.01756 0.01074 -0.0655 0.0404 0.7953
7.500 1.0380 0.01797 0.01117 -0.0650 0.0383 0.7954
7.750 1.0583 0.01846 0.01164 -0.0643 0.0359 0.7956
8.000 1.0759 0.01911 0.01229 -0.0633 0.0332 0.7960
8.250 1.0969 0.01955 0.01275 -0.0627 0.0323 0.7961
8.500 1.1169 0.02004 0.01326 -0.0621 0.0312 0.7962
8.750 1.1362 0.02057 0.01380 -0.0613 0.0300 0.7963
9.000 1.1542 0.02119 0.01443 -0.0604 0.0287 0.7964
9.250 1.1693 0.02202 0.01529 -0.0591 0.0274 0.7964
9.500 1.1890 0.02251 0.01582 -0.0584 0.0269 0.7965
9.750 1.2075 0.02310 0.01644 -0.0576 0.0263 0.7965
10.000 1.2254 0.02372 0.01709 -0.0567 0.0256 0.7966
10.250 1.2429 0.02437 0.01777 -0.0558 0.0250 0.7967
10.500 1.2599 0.02505 0.01847 -0.0549 0.0244 0.7967
10.750 1.2754 0.02584 0.01929 -0.0537 0.0237 0.7967
11.000 1.2866 0.02695 0.02043 -0.0521 0.0230 0.7968
11.250 1.2976 0.02806 0.02161 -0.0505 0.0225 0.7969
11.500 1.3144 0.02876 0.02236 -0.0496 0.0222 0.7971
11.750 1.3309 0.02949 0.02313 -0.0487 0.0218 0.7973
12.000 1.3462 0.03031 0.02400 -0.0477 0.0214 0.7974
12.250 1.3600 0.03122 0.02497 -0.0466 0.0210 0.7974
12.500 1.3735 0.03217 0.02597 -0.0454 0.0206 0.7974
12.750 1.3870 0.03313 0.02697 -0.0443 0.0203 0.7974
13.000 1.3999 0.03414 0.02802 -0.0432 0.0199 0.7974
13.250 1.4110 0.03528 0.02921 -0.0420 0.0196 0.7975
13.500 1.4206 0.03658 0.03056 -0.0406 0.0193 0.7975
13.750 1.4269 0.03819 0.03224 -0.0390 0.0189 0.7975
14.000 1.4272 0.04037 0.03452 -0.0368 0.0185 0.7975
14.250 1.4382 0.04163 0.03585 -0.0358 0.0184 0.7976
14.500 1.4488 0.04295 0.03726 -0.0348 0.0182 0.7976
14.750 1.4578 0.04443 0.03882 -0.0337 0.0180 0.7977
15.000 1.4662 0.04601 0.04049 -0.0327 0.0179 0.7977
15.250 1.4735 0.04770 0.04227 -0.0317 0.0176 0.7978
15.500 1.4799 0.04951 0.04417 -0.0307 0.0174 0.7978
15.750 1.4852 0.05147 0.04623 -0.0298 0.0173 0.7979
16.000 1.4904 0.05351 0.04836 -0.0289 0.0171 0.7979
16.250 1.4949 0.05566 0.05060 -0.0282 0.0168 0.7980
16.500 1.4992 0.05788 0.05290 -0.0277 0.0166 0.7981
16.750 1.5021 0.06029 0.05540 -0.0271 0.0165 0.7981
17.000 1.5043 0.06286 0.05806 -0.0268 0.0163 0.7982
17.250 1.5054 0.06564 0.06093 -0.0265 0.0161 0.7983
17.500 1.5051 0.06864 0.06402 -0.0264 0.0160 0.7984
17.750 1.5038 0.07186 0.06733 -0.0264 0.0159 0.7984
18.000 1.5010 0.07531 0.07088 -0.0266 0.0157 0.7985
18.250 1.4965 0.07908 0.07476 -0.0270 0.0156 0.7986
18.500 1.4901 0.08323 0.07902 -0.0277 0.0155 0.7986
18.750 1.4812 0.08782 0.08373 -0.0286 0.0154 0.7987
19.000 1.4695 0.09295 0.08898 -0.0298 0.0153 0.7987
19.250 1.4543 0.09873 0.09491 -0.0315 0.0152 0.7987
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Polar data table (+)
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