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NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
Reynolds number: 500,000
Max Cl/Cd: 80.9 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf414f-il-500000.txt
Download as CSV file: xf-nlf414f-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4566   0.08013   0.07736  -0.0701   0.8355   0.0235
 -10.250  -0.4764   0.07384   0.07096  -0.0752   0.8353   0.0235
 -10.000  -0.4952   0.06900   0.06598  -0.0781   0.8349   0.0235
  -9.750  -0.5118   0.06499   0.06181  -0.0801   0.8345   0.0235
  -9.500  -0.5251   0.05955   0.05631  -0.0807   0.8342   0.0238
  -9.250  -0.5191   0.05677   0.05351  -0.0812   0.8335   0.0240
  -9.000  -0.5129   0.05427   0.05094  -0.0816   0.8329   0.0242
  -8.750  -0.5045   0.05196   0.04855  -0.0820   0.8326   0.0245
  -8.500  -0.4948   0.04961   0.04610  -0.0823   0.8322   0.0248
  -8.250  -0.4836   0.04720   0.04354  -0.0825   0.8318   0.0254
  -8.000  -0.4715   0.04453   0.04067  -0.0825   0.8312   0.0264
  -7.750  -0.4697   0.03996   0.03534  -0.0809   0.8301   0.0290
  -7.500  -0.4495   0.03781   0.03320  -0.0813   0.8295   0.0294
  -7.250  -0.4289   0.03620   0.03152  -0.0815   0.8291   0.0301
  -7.000  -0.4168   0.02762   0.02157  -0.0779   0.8284   0.0195
  -6.750  -0.3922   0.02585   0.01970  -0.0778   0.8280   0.0191
  -6.500  -0.3680   0.02431   0.01801  -0.0775   0.8274   0.0189
  -6.250  -0.3432   0.02347   0.01699  -0.0771   0.8267   0.0191
  -6.000  -0.3182   0.02276   0.01613  -0.0768   0.8261   0.0194
  -5.750  -0.2934   0.02168   0.01499  -0.0764   0.8257   0.0195
  -5.500  -0.2693   0.02089   0.01416  -0.0760   0.8252   0.0196
  -5.250  -0.2465   0.02033   0.01360  -0.0754   0.8245   0.0199
  -5.000  -0.2188   0.01968   0.01298  -0.0764   0.8228   0.0204
  -4.750  -0.1926   0.01935   0.01267  -0.0770   0.8213   0.0211
  -4.500  -0.1671   0.01910   0.01242  -0.0774   0.8199   0.0220
  -4.250  -0.1417   0.01886   0.01217  -0.0775   0.8182   0.0231
  -4.000  -0.1172   0.01848   0.01178  -0.0775   0.8166   0.0244
  -3.750  -0.0916   0.01828   0.01159  -0.0775   0.8154   0.0265
  -3.500  -0.0659   0.01806   0.01137  -0.0775   0.8143   0.0304
  -3.250  -0.0401   0.01780   0.01115  -0.0774   0.8132   0.0396
  -3.000  -0.0156   0.01716   0.01082  -0.0772   0.8122   0.1081
  -2.750   0.0065   0.01578   0.01046  -0.0776   0.8113   0.3692
  -2.500   0.0262   0.01505   0.01105  -0.0763   0.8105   0.6815
  -2.250   0.0548   0.01567   0.01155  -0.0761   0.8099   0.7323
  -2.000   0.0785   0.01676   0.01269  -0.0765   0.8039   0.7480
  -1.750   0.1041   0.01732   0.01323  -0.0760   0.8015   0.7590
  -1.500   0.1273   0.01782   0.01378  -0.0743   0.7997   0.7694
  -1.250   0.1481   0.01854   0.01455  -0.0716   0.7983   0.7882
  -1.000   0.1683   0.01881   0.01486  -0.0690   0.7971   0.7962
  -0.750   0.1975   0.01887   0.01486  -0.0692   0.7963   0.8011
  -0.500   0.2260   0.01880   0.01475  -0.0694   0.7955   0.8039
  -0.250   0.2526   0.01875   0.01468  -0.0689   0.7948   0.8057
   0.000   0.2798   0.01876   0.01467  -0.0685   0.7942   0.8076
   0.250   0.2980   0.01938   0.01534  -0.0687   0.7846   0.8105
   0.500   0.3267   0.01935   0.01529  -0.0689   0.7831   0.8135
   0.750   0.3575   0.01926   0.01518  -0.0695   0.7819   0.8168
   1.000   0.3885   0.01905   0.01494  -0.0700   0.7810   0.8186
   1.250   0.4174   0.01876   0.01465  -0.0699   0.7802   0.8199
   1.500   0.4467   0.01854   0.01443  -0.0699   0.7795   0.8209
   1.750   0.4760   0.01833   0.01422  -0.0699   0.7788   0.8220
   2.000   0.4958   0.01883   0.01478  -0.0701   0.7688   0.8235
   2.250   0.5281   0.01824   0.01420  -0.0703   0.7672   0.8245
   2.500   0.5628   0.01723   0.01318  -0.0704   0.7660   0.8255
   2.750   0.5972   0.01620   0.01213  -0.0705   0.7648   0.8263
   3.000   0.6312   0.01516   0.01107  -0.0706   0.7635   0.8270
   3.250   0.6596   0.01477   0.01074  -0.0710   0.7551   0.8282
   3.500   0.6940   0.01355   0.00950  -0.0712   0.7514   0.8289
   3.750   0.7280   0.01248   0.00840  -0.0715   0.7485   0.8294
   4.000   0.7567   0.01227   0.00828  -0.0721   0.7391   0.8300
   4.250   0.7881   0.01166   0.00771  -0.0726   0.7315   0.8306
   4.500   0.8167   0.01160   0.00775  -0.0733   0.7133   0.8314
   4.750   0.8498   0.01054   0.00660  -0.0735   0.6791   0.8319
   5.000   0.8673   0.01072   0.00604  -0.0713   0.5620   0.8323
   5.250   0.8706   0.01239   0.00706  -0.0685   0.4417   0.8328
   5.500   0.8713   0.01403   0.00818  -0.0658   0.3420   0.8333
   5.750   0.8734   0.01545   0.00915  -0.0631   0.2562   0.8338
   6.000   0.8833   0.01661   0.00992  -0.0613   0.1873   0.8345
   6.250   0.8980   0.01746   0.01055  -0.0601   0.1465   0.8349
   6.500   0.9146   0.01821   0.01113  -0.0591   0.1153   0.8351
   6.750   0.9313   0.01896   0.01170  -0.0581   0.0884   0.8353
   7.000   0.9481   0.01969   0.01230  -0.0570   0.0701   0.8354
   7.250   0.9660   0.02035   0.01290  -0.0561   0.0602   0.8357
   7.500   0.9843   0.02098   0.01353  -0.0552   0.0543   0.8362
   7.750   1.0018   0.02167   0.01420  -0.0543   0.0498   0.8365
   8.000   1.0193   0.02238   0.01493  -0.0533   0.0468   0.8366
   8.250   1.0383   0.02298   0.01556  -0.0526   0.0443   0.8367
   8.500   1.0553   0.02372   0.01629  -0.0516   0.0419   0.8367
   8.750   1.0685   0.02473   0.01731  -0.0502   0.0398   0.8370
   9.000   1.0868   0.02537   0.01801  -0.0493   0.0387   0.8374
   9.250   1.1041   0.02609   0.01878  -0.0484   0.0373   0.8375
   9.500   1.1210   0.02685   0.01957  -0.0475   0.0361   0.8375
   9.750   1.1368   0.02769   0.02042  -0.0465   0.0350   0.8376
  10.000   1.1489   0.02885   0.02159  -0.0449   0.0338   0.8376
  10.250   1.1631   0.02987   0.02267  -0.0437   0.0329   0.8376
  10.500   1.1803   0.03064   0.02351  -0.0428   0.0322   0.8376
  10.750   1.1966   0.03150   0.02443  -0.0418   0.0314   0.8376
  11.000   1.2125   0.03240   0.02538  -0.0409   0.0306   0.8377
  11.250   1.2281   0.03332   0.02636  -0.0399   0.0299   0.8377
  11.500   1.2432   0.03429   0.02737  -0.0389   0.0293   0.8378
  11.750   1.2578   0.03534   0.02845  -0.0378   0.0287   0.8378
  12.000   1.2726   0.03658   0.02971  -0.0367   0.0280   0.8378
  12.250   1.2896   0.03799   0.03121  -0.0355   0.0274   0.8380
  12.500   1.3029   0.03904   0.03238  -0.0345   0.0270   0.8383
  12.750   1.3160   0.04020   0.03366  -0.0334   0.0265   0.8385
  13.000   1.3291   0.04147   0.03504  -0.0324   0.0260   0.8386
  13.250   1.3415   0.04282   0.03650  -0.0313   0.0256   0.8387
  13.500   1.3530   0.04424   0.03802  -0.0302   0.0252   0.8387
  13.750   1.3630   0.04577   0.03967  -0.0290   0.0248   0.8388
  14.000   1.3716   0.04739   0.04140  -0.0278   0.0244   0.8389
  14.250   1.3794   0.04908   0.04319  -0.0267   0.0241   0.8389
  14.500   1.3861   0.05087   0.04507  -0.0255   0.0238   0.8390
  14.750   1.3920   0.05278   0.04708  -0.0244   0.0235   0.8391
  15.000   1.3972   0.05490   0.04930  -0.0232   0.0233   0.8392
  15.250   1.4001   0.05750   0.05202  -0.0220   0.0230   0.8393
  15.500   1.3963   0.06110   0.05583  -0.0205   0.0228   0.8394
  15.750   1.3851   0.06528   0.06026  -0.0190   0.0226   0.8394
  16.000   1.3753   0.06873   0.06391  -0.0181   0.0225   0.8395
  16.250   1.3641   0.07253   0.06792  -0.0176   0.0225   0.8395
  16.500   1.3511   0.07683   0.07242  -0.0175   0.0224   0.8396
  16.750   1.3360   0.08173   0.07754  -0.0179   0.0223   0.8396
  17.000   1.3186   0.08723   0.08325  -0.0190   0.0222   0.8397
  17.250   1.2992   0.09346   0.08970  -0.0208   0.0221   0.8397
  17.500   1.2767   0.10065   0.09710  -0.0235   0.0221   0.8397
  17.750   1.2516   0.10886   0.10553  -0.0274   0.0221   0.8397
  18.000   1.2228   0.11840   0.11529  -0.0327   0.0222   0.8396
  18.250   1.1890   0.12989   0.12699  -0.0397   0.0223   0.8395
  18.500   1.1434   0.14555   0.14287  -0.0502   0.0225   0.8393
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