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NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(2)-415 (naca662415-il)
Reynolds number: 200,000
Max Cl/Cd: 55.31 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca662415-il-200000-n5.txt
Download as CSV file: xf-naca662415-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-415                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3884   0.08377   0.07990  -0.0975   0.9556   0.0237
 -12.000  -0.4388   0.06521   0.06110  -0.1130   0.9478   0.0229
 -11.750  -0.4705   0.05732   0.05291  -0.1179   0.9372   0.0227
 -11.500  -0.4878   0.05278   0.04813  -0.1192   0.9275   0.0229
 -11.250  -0.5040   0.04886   0.04392  -0.1190   0.9185   0.0230
 -11.000  -0.5196   0.04578   0.04059  -0.1168   0.9090   0.0231
 -10.500  -0.5438   0.04075   0.03500  -0.1101   0.8933   0.0234
 -10.250  -0.5500   0.03850   0.03243  -0.1066   0.8875   0.0238
 -10.000  -0.5501   0.03628   0.02988  -0.1037   0.8820   0.0241
  -9.750  -0.5467   0.03421   0.02744  -0.1010   0.8765   0.0245
  -9.500  -0.5400   0.03233   0.02510  -0.0985   0.8722   0.0253
  -9.250  -0.5268   0.03065   0.02314  -0.0970   0.8689   0.0259
  -9.000  -0.5103   0.02934   0.02172  -0.0960   0.8650   0.0264
  -8.750  -0.4920   0.02816   0.02039  -0.0951   0.8614   0.0269
  -8.500  -0.4718   0.02703   0.01909  -0.0944   0.8584   0.0275
  -8.250  -0.4498   0.02591   0.01781  -0.0939   0.8560   0.0281
  -8.000  -0.4263   0.02483   0.01655  -0.0935   0.8539   0.0288
  -7.750  -0.4039   0.02396   0.01554  -0.0930   0.8510   0.0297
  -7.500  -0.3814   0.02324   0.01464  -0.0924   0.8480   0.0308
  -7.250  -0.3577   0.02253   0.01380  -0.0920   0.8452   0.0315
  -7.000  -0.3315   0.02138   0.01266  -0.0921   0.8429   0.0324
  -6.750  -0.3076   0.02065   0.01190  -0.0918   0.8407   0.0334
  -6.500  -0.2841   0.01999   0.01121  -0.0914   0.8386   0.0343
  -6.250  -0.2622   0.01947   0.01065  -0.0907   0.8363   0.0356
  -6.000  -0.2423   0.01906   0.01021  -0.0896   0.8333   0.0371
  -5.750  -0.2219   0.01866   0.00975  -0.0886   0.8306   0.0384
  -5.500  -0.2034   0.01811   0.00919  -0.0874   0.8281   0.0396
  -5.250  -0.1845   0.01761   0.00869  -0.0862   0.8258   0.0410
  -5.000  -0.1639   0.01722   0.00825  -0.0853   0.8239   0.0429
  -4.750  -0.1419   0.01689   0.00787  -0.0845   0.8223   0.0455
  -4.500  -0.1212   0.01662   0.00756  -0.0836   0.8202   0.0480
  -4.250  -0.1030   0.01636   0.00731  -0.0822   0.8173   0.0513
  -4.000  -0.0824   0.01614   0.00707  -0.0812   0.8147   0.0556
  -3.750  -0.0615   0.01586   0.00683  -0.0803   0.8122   0.0651
  -3.500  -0.0419   0.01540   0.00655  -0.0792   0.8102   0.1016
  -3.250  -0.0292   0.01437   0.00618  -0.0774   0.8083   0.2591
  -3.000  -0.0211   0.01299   0.00581  -0.0749   0.8065   0.4932
  -2.750  -0.0054   0.01298   0.00655  -0.0718   0.8047   0.6828
  -2.500   0.0143   0.01350   0.00715  -0.0698   0.8021   0.7252
  -2.250   0.0358   0.01396   0.00759  -0.0683   0.7997   0.7486
  -2.000   0.0591   0.01437   0.00800  -0.0669   0.7976   0.7612
  -1.750   0.0830   0.01472   0.00833  -0.0657   0.7956   0.7728
  -1.500   0.1080   0.01493   0.00847  -0.0650   0.7940   0.7840
  -1.250   0.1340   0.01512   0.00865  -0.0644   0.7927   0.7879
  -1.000   0.1614   0.01517   0.00865  -0.0645   0.7915   0.7909
  -0.750   0.1895   0.01518   0.00861  -0.0648   0.7904   0.7939
  -0.500   0.2141   0.01524   0.00863  -0.0647   0.7886   0.7974
  -0.250   0.2325   0.01540   0.00878  -0.0636   0.7849   0.8006
   0.000   0.2551   0.01553   0.00892  -0.0629   0.7825   0.8020
   0.250   0.2800   0.01561   0.00898  -0.0626   0.7803   0.8036
   0.500   0.3071   0.01563   0.00900  -0.0627   0.7785   0.8054
   0.750   0.3360   0.01560   0.00896  -0.0632   0.7768   0.8070
   1.000   0.3664   0.01554   0.00889  -0.0640   0.7754   0.8086
   1.250   0.3975   0.01548   0.00882  -0.0649   0.7742   0.8103
   1.500   0.4084   0.01586   0.00925  -0.0623   0.7684   0.8132
   1.750   0.4332   0.01592   0.00933  -0.0622   0.7652   0.8158
   2.000   0.4617   0.01588   0.00931  -0.0626   0.7628   0.8175
   2.250   0.4923   0.01579   0.00927  -0.0632   0.7609   0.8188
   2.500   0.5244   0.01569   0.00919  -0.0641   0.7592   0.8201
   2.750   0.5384   0.01600   0.00958  -0.0619   0.7540   0.8222
   3.000   0.5594   0.01613   0.00977  -0.0610   0.7496   0.8244
   3.250   0.5895   0.01603   0.00973  -0.0615   0.7468   0.8262
   3.500   0.6250   0.01576   0.00951  -0.0630   0.7443   0.8278
   3.750   0.6429   0.01578   0.00960  -0.0614   0.7366   0.8306
   4.000   0.6837   0.01502   0.00886  -0.0633   0.7287   0.8324
   4.250   0.7006   0.01481   0.00873  -0.0610   0.7167   0.8347
   4.500   0.7217   0.01451   0.00850  -0.0594   0.7040   0.8368
   4.750   0.7412   0.01428   0.00834  -0.0576   0.6893   0.8392
   5.000   0.7597   0.01393   0.00800  -0.0554   0.6653   0.8420
   5.250   0.7649   0.01383   0.00788  -0.0509   0.6234   0.8458
   5.750   0.7710   0.01484   0.00771  -0.0414   0.4287   0.8524
   6.000   0.7633   0.01597   0.00851  -0.0357   0.3600   0.8568
   6.250   0.7577   0.01725   0.00942  -0.0309   0.2895   0.8618
   6.500   0.7544   0.01860   0.01039  -0.0267   0.2161   0.8665
   6.750   0.7531   0.01992   0.01135  -0.0229   0.1439   0.8709
   7.000   0.7561   0.02121   0.01230  -0.0199   0.0847   0.8756
   7.250   0.7668   0.02219   0.01314  -0.0180   0.0593   0.8802
   7.500   0.7788   0.02297   0.01389  -0.0161   0.0496   0.8840
   7.750   0.7927   0.02367   0.01463  -0.0145   0.0445   0.8885
   8.000   0.8063   0.02449   0.01546  -0.0131   0.0412   0.8936
   8.250   0.8213   0.02520   0.01626  -0.0118   0.0385   0.8984
   8.500   0.8344   0.02598   0.01711  -0.0102   0.0361   0.9038
   8.750   0.8453   0.02701   0.01818  -0.0086   0.0341   0.9103
   9.000   0.8581   0.02783   0.01909  -0.0070   0.0327   0.9170
   9.250   0.8713   0.02869   0.02003  -0.0056   0.0311   0.9250
   9.500   0.8839   0.02959   0.02100  -0.0042   0.0295   0.9338
   9.750   0.8967   0.03059   0.02206  -0.0031   0.0283   0.9441
  10.000   0.9093   0.03190   0.02338  -0.0022   0.0273   0.9565
  10.250   0.9279   0.03283   0.02445  -0.0022   0.0264   0.9801
  10.750   0.9617   0.03502   0.02678  -0.0012   0.0247   1.0000
  11.000   0.9790   0.03615   0.02797  -0.0008   0.0238   1.0000
  11.250   0.9959   0.03732   0.02916  -0.0005   0.0230   1.0000
  11.500   1.0133   0.03859   0.03041  -0.0002   0.0222   1.0000
  11.750   1.0316   0.03984   0.03177   0.0002   0.0216   1.0000
  12.000   1.0499   0.04115   0.03322   0.0005   0.0209   1.0000
  12.250   1.0679   0.04256   0.03478   0.0009   0.0204   1.0000
  12.500   1.0851   0.04411   0.03647   0.0013   0.0200   1.0000
  12.750   1.0999   0.04573   0.03826   0.0018   0.0195   1.0000
  13.000   1.1129   0.04751   0.04019   0.0024   0.0191   1.0000
  13.250   1.1243   0.04942   0.04226   0.0030   0.0188   1.0000
  13.500   1.1333   0.05145   0.04444   0.0037   0.0186   1.0000
  13.750   1.1404   0.05358   0.04673   0.0044   0.0183   1.0000
  14.000   1.1457   0.05597   0.04928   0.0052   0.0182   1.0000
  14.250   1.1490   0.05849   0.05196   0.0058   0.0180   1.0000
  14.500   1.1502   0.06128   0.05492   0.0065   0.0178   1.0000
  14.750   1.1494   0.06436   0.05817   0.0070   0.0177   1.0000
  15.000   1.1404   0.06812   0.06219   0.0075   0.0175   1.0000
  15.250   1.1284   0.07229   0.06664   0.0078   0.0174   1.0000
  15.500   1.1130   0.07705   0.07169   0.0076   0.0173   1.0000
  15.750   1.0968   0.08226   0.07716   0.0068   0.0173   1.0000
  16.000   1.0768   0.08825   0.08343   0.0052   0.0171   1.0000
  16.250   1.0566   0.09476   0.09019   0.0028   0.0171   1.0000
  16.500   1.0334   0.10233   0.09801  -0.0006   0.0170   1.0000
  16.750   1.0115   0.11036   0.10624  -0.0049   0.0171   1.0000
  17.000   0.9856   0.11992   0.11601  -0.0106   0.0172   1.0000
  17.250   0.9576   0.13101   0.12728  -0.0178   0.0173   1.0000
  17.500   0.9294   0.14347   0.13988  -0.0258   0.0175   1.0000
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