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NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
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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