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NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)
Reynolds number: 200,000
Max Cl/Cd: 36.17 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf415-il-200000.txt
Download as CSV file: xf-nlf415-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3666   0.10017   0.09652  -0.1058   0.9612   0.0515
 -11.250  -0.3842   0.09337   0.08967  -0.1116   0.9597   0.0518
 -11.000  -0.4137   0.09183   0.08816  -0.1067   0.9557   0.0517
 -10.750  -0.4377   0.08869   0.08500  -0.1057   0.9534   0.0517
 -10.500  -0.4632   0.08565   0.08192  -0.1047   0.9515   0.0517
 -10.250  -0.4887   0.08303   0.07924  -0.1032   0.9499   0.0517
 -10.000  -0.5141   0.08052   0.07663  -0.1022   0.9481   0.0518
  -9.750  -0.5398   0.07898   0.07504  -0.0987   0.9472   0.0518
  -9.500  -0.5683   0.07804   0.07406  -0.0933   0.9466   0.0517
  -9.250  -0.5942   0.07694   0.07295  -0.0872   0.9467   0.0516
  -9.000  -0.7178   0.08853   0.08539  -0.0392   1.0000   0.0448
  -8.750  -0.7709   0.08533   0.08207  -0.0356   1.0000   0.0434
  -8.500  -0.7957   0.08217   0.07879  -0.0332   1.0000   0.0433
  -8.250  -0.8044   0.07924   0.07580  -0.0313   1.0000   0.0442
  -8.000  -0.8119   0.07629   0.07277  -0.0295   1.0000   0.0453
  -7.750  -0.8185   0.07305   0.06939  -0.0279   1.0000   0.0465
  -7.500  -0.8209   0.06977   0.06591  -0.0266   0.9998   0.0483
  -7.250  -0.8141   0.07062   0.06593  -0.0257   0.9973   0.0525
  -7.000  -0.8116   0.06159   0.05681  -0.0269   0.9960   0.0542
  -6.750  -0.7952   0.05810   0.05336  -0.0276   0.9948   0.0561
  -6.500  -0.7821   0.05547   0.05061  -0.0272   0.9942   0.0586
  -6.250  -0.7615   0.05822   0.05253  -0.0258   0.9916   0.0657
  -6.000  -0.7510   0.04960   0.04405  -0.0269   0.9908   0.0689
  -5.750  -0.7295   0.04734   0.04172  -0.0275   0.9889   0.0730
  -5.500  -0.7070   0.04491   0.03892  -0.0284   0.9872   0.0833
  -5.250  -0.6826   0.04360   0.03726  -0.0293   0.9859   0.0958
  -5.000  -0.6590   0.04177   0.03530  -0.0302   0.9850   0.1104
  -4.750  -0.6397   0.03968   0.03323  -0.0305   0.9845   0.1267
  -4.500  -0.5992   0.03535   0.02791  -0.0259   0.9839   0.0577
  -4.250  -0.5707   0.03382   0.02578  -0.0233   0.9814   0.0412
  -4.000  -0.5466   0.03182   0.02376  -0.0226   0.9801   0.0395
  -3.750  -0.5215   0.03065   0.02250  -0.0221   0.9785   0.0389
  -3.500  -0.4954   0.02992   0.02171  -0.0219   0.9769   0.0390
  -3.250  -0.4671   0.02970   0.02140  -0.0224   0.9753   0.0403
  -3.000  -0.4393   0.02945   0.02113  -0.0228   0.9742   0.0406
  -2.750  -0.4114   0.02930   0.02097  -0.0234   0.9734   0.0408
  -2.500  -0.3846   0.02885   0.02052  -0.0241   0.9728   0.0421
  -2.250  -0.3696   0.02734   0.01898  -0.0227   0.9687   0.0442
  -2.000  -0.3416   0.02712   0.01868  -0.0236   0.9658   0.0475
  -1.500  -0.2839   0.02557   0.01911  -0.0270   0.9632   0.5848
  -1.250  -0.2569   0.02835   0.02209  -0.0251   0.9606   0.6438
  -1.000  -0.2479   0.02857   0.02237  -0.0211   0.9557   0.6644
  -0.750  -0.2248   0.02945   0.02329  -0.0197   0.9510   0.6787
  -0.500  -0.1992   0.03063   0.02451  -0.0187   0.9485   0.6911
  -0.250  -0.1723   0.03254   0.02644  -0.0178   0.9468   0.7112
   0.000  -0.1648   0.03152   0.02543  -0.0145   0.9395   0.7134
   0.250  -0.1348   0.03195   0.02581  -0.0157   0.9362   0.7151
   0.500  -0.0996   0.03264   0.02641  -0.0182   0.9341   0.7152
   0.750  -0.0631   0.03382   0.02752  -0.0210   0.9328   0.7154
   1.000  -0.0542   0.03265   0.02632  -0.0185   0.9239   0.7160
   1.250  -0.0208   0.03323   0.02685  -0.0205   0.9209   0.7168
   1.500   0.0169   0.03428   0.02786  -0.0234   0.9189   0.7173
   1.750   0.0285   0.03367   0.02724  -0.0215   0.9101   0.7178
   2.000   0.0642   0.03427   0.02782  -0.0239   0.9062   0.7183
   2.250   0.1058   0.03549   0.02904  -0.0274   0.9040   0.7189
   2.500   0.1201   0.03485   0.02839  -0.0259   0.8927   0.7195
   2.750   0.1506   0.03520   0.02875  -0.0272   0.8841   0.7201
   3.000   0.2078   0.03485   0.02841  -0.0320   0.8634   0.7209
   3.250   0.2459   0.03475   0.02833  -0.0340   0.8511   0.7217
   3.500   0.2905   0.03500   0.02863  -0.0374   0.8465   0.7230
   3.750   0.3187   0.03480   0.02847  -0.0378   0.8348   0.7241
   4.000   0.3835   0.03353   0.02727  -0.0430   0.8190   0.7251
   4.250   0.4572   0.03132   0.02516  -0.0490   0.8036   0.7260
   4.500   0.5012   0.03003   0.02397  -0.0509   0.7922   0.7269
   4.750   0.5689   0.02809   0.02222  -0.0565   0.7876   0.7279
   5.000   0.5979   0.02717   0.02142  -0.0561   0.7760   0.7291
   5.250   0.6367   0.02568   0.02009  -0.0570   0.7643   0.7303
   5.500   0.6756   0.02384   0.01841  -0.0575   0.7487   0.7317
   5.750   0.6896   0.02318   0.01786  -0.0546   0.7250   0.7331
   6.000   0.6955   0.02302   0.01779  -0.0507   0.6849   0.7347
   6.250   0.7418   0.02051   0.01258  -0.0494   0.2381   0.7360
   6.500   0.7462   0.02185   0.01345  -0.0463   0.1721   0.7377
   6.750   0.7584   0.02286   0.01423  -0.0444   0.1412   0.7396
   7.000   0.7738   0.02365   0.01497  -0.0429   0.1218   0.7413
   7.250   0.7903   0.02444   0.01573  -0.0415   0.1086   0.7429
   7.500   0.8081   0.02528   0.01651  -0.0404   0.0980   0.7446
   7.750   0.8290   0.02590   0.01720  -0.0397   0.0899   0.7465
   8.000   0.8525   0.02678   0.01806  -0.0393   0.0831   0.7485
   8.250   0.8754   0.02741   0.01875  -0.0390   0.0765   0.7508
   8.500   0.9041   0.02834   0.01970  -0.0395   0.0701   0.7531
   8.750   0.9225   0.02887   0.02030  -0.0386   0.0636   0.7555
   9.000   0.9451   0.02970   0.02121  -0.0383   0.0567   0.7577
   9.250   0.9627   0.03032   0.02190  -0.0373   0.0510   0.7602
   9.500   0.9853   0.03135   0.02308  -0.0369   0.0441   0.7631
   9.750   1.0149   0.03294   0.02466  -0.0377   0.0376   0.7662
  10.000   1.0392   0.03413   0.02610  -0.0373   0.0337   0.7696
  10.250   1.0610   0.03536   0.02740  -0.0369   0.0309   0.7728
  10.500   1.0913   0.03783   0.03019  -0.0375   0.0282   0.7765
  10.750   1.1097   0.03962   0.03232  -0.0365   0.0263   0.7807
  11.000   1.1274   0.04180   0.03479  -0.0355   0.0253   0.7851
  11.250   1.1392   0.04408   0.03738  -0.0338   0.0245   0.7891
  11.500   1.1464   0.04665   0.04027  -0.0316   0.0241   0.7939
  11.750   1.1491   0.04954   0.04345  -0.0291   0.0237   0.7991
  12.000   1.1452   0.05278   0.04707  -0.0260   0.0236   0.8038
  12.250   1.1335   0.05665   0.05135  -0.0223   0.0237   0.8091
  12.500   1.1136   0.06118   0.05631  -0.0183   0.0239   0.8146
  12.750   1.0586   0.06964   0.06546  -0.0126   0.0251   0.8168
  13.000   1.0221   0.07621   0.07240  -0.0100   0.0259   0.8208
  13.250   0.9908   0.08240   0.07886  -0.0091   0.0263   0.8262
  13.500   0.9594   0.08906   0.08576  -0.0095   0.0267   0.8320
  13.750   0.9287   0.09650   0.09340  -0.0118   0.0272   0.8390
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