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NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
Reynolds number: 100,000
Max Cl/Cd: 34.4 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf414f-il-100000-n5.txt
Download as CSV file: xf-nlf414f-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3692   0.09964   0.09419  -0.0755   0.8857   0.0339
 -10.750  -0.3640   0.09622   0.09078  -0.0770   0.8854   0.0332
 -10.500  -0.3635   0.09138   0.08594  -0.0801   0.8851   0.0324
 -10.000  -0.4253   0.06962   0.06380  -0.0979   0.8831   0.0284
  -9.750  -0.4296   0.06613   0.06022  -0.0995   0.8821   0.0282
  -9.500  -0.4365   0.06298   0.05695  -0.1004   0.8812   0.0280
  -9.250  -0.4432   0.06011   0.05391  -0.1003   0.8803   0.0278
  -9.000  -0.4465   0.05715   0.05075  -0.1000   0.8794   0.0276
  -8.750  -0.4476   0.05430   0.04765  -0.0992   0.8781   0.0274
  -8.500  -0.4467   0.05154   0.04460  -0.0980   0.8765   0.0272
  -8.250  -0.4432   0.04890   0.04165  -0.0967   0.8752   0.0270
  -8.000  -0.4373   0.04640   0.03881  -0.0952   0.8742   0.0269
  -7.750  -0.4287   0.04406   0.03611  -0.0937   0.8731   0.0268
  -7.500  -0.4168   0.04188   0.03356  -0.0922   0.8719   0.0268
  -7.250  -0.4017   0.03986   0.03118  -0.0910   0.8707   0.0270
  -7.000  -0.3840   0.03804   0.02900  -0.0899   0.8697   0.0272
  -6.750  -0.3672   0.03652   0.02715  -0.0886   0.8687   0.0275
  -6.500  -0.3517   0.03532   0.02563  -0.0869   0.8673   0.0282
  -6.250  -0.3363   0.03438   0.02464  -0.0855   0.8654   0.0293
  -6.000  -0.3193   0.03366   0.02386  -0.0842   0.8636   0.0306
  -5.750  -0.3006   0.03285   0.02292  -0.0830   0.8624   0.0319
  -5.500  -0.2804   0.03199   0.02193  -0.0818   0.8610   0.0328
  -5.250  -0.2589   0.03118   0.02100  -0.0807   0.8595   0.0338
  -5.000  -0.2375   0.03039   0.02020  -0.0798   0.8580   0.0350
  -4.750  -0.2167   0.02978   0.01960  -0.0790   0.8568   0.0367
  -4.500  -0.1953   0.02931   0.01909  -0.0782   0.8557   0.0395
  -4.250  -0.1729   0.02884   0.01862  -0.0776   0.8547   0.0436
  -4.000  -0.1664   0.02868   0.01844  -0.0745   0.8511   0.0471
  -3.750  -0.1524   0.02836   0.01809  -0.0726   0.8487   0.0518
  -3.500  -0.1341   0.02805   0.01779  -0.0714   0.8465   0.0620
  -3.250  -0.1127   0.02761   0.01747  -0.0707   0.8444   0.0856
  -3.000  -0.0943   0.02626   0.01719  -0.0701   0.8427   0.2756
  -2.750  -0.0961   0.02619   0.01906  -0.0618   0.8409   0.6302
  -2.500  -0.0709   0.02733   0.01999  -0.0612   0.8390   0.7419
  -2.250  -0.0732   0.02816   0.02080  -0.0549   0.8338   0.7748
  -2.000  -0.0730   0.02896   0.02165  -0.0470   0.8306   0.8079
  -1.750  -0.0649   0.02939   0.02205  -0.0410   0.8280   0.8367
  -1.500  -0.0405   0.02953   0.02204  -0.0401   0.8262   0.8474
  -1.250  -0.0117   0.02962   0.02198  -0.0405   0.8248   0.8515
  -1.000  -0.0101   0.02961   0.02193  -0.0364   0.8188   0.8572
  -0.750   0.0120   0.02970   0.02191  -0.0360   0.8156   0.8622
  -0.500   0.0381   0.02978   0.02187  -0.0361   0.8130   0.8660
  -0.250   0.0669   0.02988   0.02188  -0.0365   0.8111   0.8691
   0.000   0.0985   0.03003   0.02194  -0.0375   0.8095   0.8716
   0.250   0.1056   0.03016   0.02204  -0.0350   0.8028   0.8754
   0.500   0.1319   0.03032   0.02214  -0.0355   0.7993   0.8777
   0.750   0.1622   0.03048   0.02224  -0.0365   0.7967   0.8795
   1.000   0.1938   0.03060   0.02231  -0.0375   0.7947   0.8809
   1.250   0.2078   0.03081   0.02252  -0.0359   0.7884   0.8831
   1.500   0.2327   0.03097   0.02266  -0.0361   0.7839   0.8847
   1.750   0.2632   0.03110   0.02277  -0.0369   0.7810   0.8861
   2.000   0.2964   0.03122   0.02289  -0.0382   0.7789   0.8872
   2.250   0.3101   0.03154   0.02322  -0.0369   0.7710   0.8887
   2.500   0.3388   0.03169   0.02339  -0.0376   0.7670   0.8899
   2.750   0.3718   0.03178   0.02351  -0.0388   0.7643   0.8910
   3.000   0.3913   0.03207   0.02383  -0.0384   0.7571   0.8923
   3.250   0.4195   0.03220   0.02402  -0.0391   0.7521   0.8930
   3.500   0.4535   0.03221   0.02408  -0.0404   0.7492   0.8935
   3.750   0.4717   0.03250   0.02444  -0.0398   0.7406   0.8948
   4.000   0.5028   0.03241   0.02444  -0.0405   0.7363   0.8957
   4.250   0.5239   0.03252   0.02462  -0.0400   0.7279   0.8968
   4.500   0.5561   0.03226   0.02446  -0.0407   0.7225   0.8973
   4.750   0.5796   0.03198   0.02428  -0.0402   0.7113   0.8980
   5.000   0.6084   0.03105   0.02344  -0.0397   0.6975   0.8988
   5.250   0.6377   0.03001   0.02250  -0.0392   0.6824   0.8998
   5.500   0.6637   0.02941   0.02201  -0.0386   0.6678   0.9010
   6.000   0.7117   0.02854   0.02138  -0.0372   0.6301   0.9027
   6.250   0.7388   0.02779   0.02071  -0.0365   0.5988   0.9033
   6.500   0.7926   0.02478   0.01746  -0.0368   0.5247   0.9036
   6.750   0.8224   0.02391   0.01563  -0.0348   0.3833   0.9042
   7.250   0.8395   0.02650   0.01704  -0.0307   0.2020   0.9068
   7.500   0.8541   0.02759   0.01783  -0.0297   0.1574   0.9075
   7.750   0.8703   0.02859   0.01866  -0.0288   0.1280   0.9083
   8.000   0.8864   0.02961   0.01955  -0.0280   0.1080   0.9091
   8.250   0.9027   0.03062   0.02051  -0.0272   0.0940   0.9099
   8.500   0.9189   0.03157   0.02148  -0.0263   0.0839   0.9108
   8.750   0.9339   0.03263   0.02253  -0.0253   0.0771   0.9118
   9.000   0.9497   0.03362   0.02357  -0.0243   0.0713   0.9130
   9.250   0.9641   0.03475   0.02470  -0.0233   0.0669   0.9145
   9.500   0.9807   0.03574   0.02579  -0.0224   0.0627   0.9161
   9.750   0.9967   0.03682   0.02692  -0.0215   0.0597   0.9177
  10.000   1.0125   0.03807   0.02812  -0.0206   0.0574   0.9191
  10.250   1.0322   0.03910   0.02934  -0.0200   0.0548   0.9205
  10.500   1.0510   0.04020   0.03054  -0.0194   0.0522   0.9220
  10.750   1.0687   0.04137   0.03175  -0.0188   0.0500   0.9237
  11.000   1.0885   0.04266   0.03304  -0.0184   0.0484   0.9254
  11.250   1.1107   0.04399   0.03453  -0.0179   0.0471   0.9275
  11.500   1.1314   0.04543   0.03620  -0.0174   0.0456   0.9301
  11.750   1.1492   0.04696   0.03794  -0.0168   0.0441   0.9335
  12.000   1.1642   0.04851   0.03967  -0.0161   0.0427   0.9380
  12.500   1.1908   0.05170   0.04306  -0.0144   0.0406   0.9738
  12.750   1.2058   0.05401   0.04555  -0.0141   0.0399   1.0000
  13.000   1.2120   0.05668   0.04859  -0.0130   0.0393   1.0000
  13.250   1.2143   0.05963   0.05189  -0.0118   0.0388   1.0000
  13.500   1.2119   0.06284   0.05545  -0.0105   0.0383   1.0000
  13.750   1.2056   0.06630   0.05924  -0.0092   0.0378   1.0000
  14.000   1.1961   0.07004   0.06328  -0.0081   0.0374   1.0000
  14.250   1.1836   0.07409   0.06763  -0.0073   0.0370   1.0000
  14.500   1.1683   0.07852   0.07234  -0.0069   0.0367   1.0000
  14.750   1.1500   0.08348   0.07757  -0.0071   0.0364   1.0000
  15.000   1.1280   0.08924   0.08360  -0.0080   0.0363   1.0000
  15.250   1.1014   0.09622   0.09086  -0.0102   0.0363   1.0000
  15.500   1.0672   0.10542   0.10036  -0.0145   0.0365   1.0000
  15.750   1.0173   0.11967   0.11491  -0.0231   0.0371   1.0000
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